# A Novel Neural Network-Based SINS/DVL Integrated Navigation Approach to Deal with DVL Malfunction for Underwater Vehicles

Authors: Wanli Li; Mingjian Chen; Chao Zhang; Lundong Zhang; Rui Chen
Journal: Mathematical Problems in Engineering
 (2020)

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## Abstract

A navigation grade Strapdown Inertial Navigation System (SINS) combined with a Doppler Velocity Log (DVL) is widely used for autonomous navigation of underwater vehicles. Whether the DVL is able to provide continuous velocity measurements is of crucial importance to the integrated navigation precision. Considering that the DVL may fail during the missions, a novel neural network-based SINS/DVL integrated navigation approach is proposed. The nonlinear autoregressive exogenous (NARX) neural network, which is able to provide reliable predictions, is employed. While the DVL is available, the neural network is trained by the body frame velocity and its increment from the SINS and the DVL measurements. Once the DVL fails, the well trained network is able to forecast the velocity which can be used for the subsequent navigation. From the experimental results, it is clearly shown that the neural network is able to provide reliable velocity predictions for about 200 s–300 s during DVL malfunction and hence maintain the short-term accuracy of the integrated navigation.


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## Body

## 1. Introduction

The ocean covers 71% of the surface of the Earth. It is rich in biological resource and minerals resource. Underwater vehicles, including remotely operated vehicles (ROVs) and autonomous underwater vehicles (AUVs), are widely used in the exploration of the ocean. However, the lack of reliable navigation techniques is still a key fact which limits the application of the underwater vehicles. Although Global Navigation Satellite System (GNSS) is widely used in surface and air navigation [1], its signals rapidly attenuate in water. The acoustic navigation systems [2], such as Long Baseline (LBL) and Ultra Short Baseline (USBL), have a limited range. For example, the 12 kHz LBL typically operates at up to 10 km ranges [3]. Strapdown Inertial Navigation System (SINS), which is able to provide complete navigation parameters, such as position, velocity, and attitude, is usually employed in autonomous underwater navigation. However, as the positioning errors of the SINS increase with time, an external aiding sensor is necessary.Based on Doppler Effect, the Doppler Velocity Log (DVL) is able to provide velocity measurements relative to the seafloor. It is regarded as one of the most potential aiding sensors which are able to limit the error growth of SINS [4, 5]. However, the DVL provide velocities in the Doppler instrumental frame, but not the geodetic frame. There are still challenges in DVL aided integrated navigation. For example,, misalignments between the SINS body frame and Doppler instrumental frame will occur during manufacture [6]. Therefore, a calibration process is usually required before conducting a mission [7, 8]. Even so, the position error of SINS/DVL will accumulate without any external position observations. Furthermore, the azimuth error of the integrated navigation shows slow convergence in the case of DVL aiding. Fast SINS in-motion initial alignment is also a challenge issue which has aroused great attention [9].In addition, DVL has a limited maximum range. Table1 shows the specifications of the DVLs [10] produced by Teledyne RD Instruments, Inc. As can be seen from the table, DVL working at a higher operating rate can provide more accurate velocity measurements, whereas its maximum range is smaller and vice versa. In the case that the acoustic wave emitted by the DVL cannot reach the seafloor, the DVL will work in the mode of water-tracked, which provides water reference velocities, or fail to provide velocities.Table 1
Specifications of the RDI workhorse navigator Doppler Velocity Log.
Parameter itemWHN 300WHN 600WHN 1200Long-term accuracy±0.4%V ± 0.2 cm/s±0.2%V ± 0.1 cm/s±0.2%V ± 0.1 cm/sOperating rate300 kHz600 kHz1200 kHzMaximum range200 m90 m25 mVelocity range±10 m/s±10 m/s±10 m/sSINS/DVL integrated is typically accomplished by using a Kalman filter (KF), which fuses the data from the SINS and the DVL. Therefore, the accuracy of the DVL measurements is of vital importance in optimally estimating the subsequent navigation solutions. In [11], the authors proposed a pretreatment method for the velocity of DVL based on the motion constraint of underwater vehicles. It is able to restrain random noise in the DVL. Adaptive Kalman filter (AKF) is also regarded as an effective approach to deal with the accuracy decrease of the DVL [12, 13]. SINS/DVL integrated navigation, in case that only partial DVL measurements are available, is also investigated. In [14, 15], tightly coupled navigation structures are proposed to deal with the situation that DVL has fewer than three beam measurements.Under certain conditions, such as sailing across sea creatures or the DVL exceeds its maximum measuring range, the DVL will fail to maintain bottom-lock and provide velocity updates [16, 17]. To circumvent this problem, Tal et al. [18] derived an extended loosely coupled (ELC) approach which is able to provide virtual vehicle velocity by using partial raw data of the DVL and additional information. In [19], the authors proposed a hybrid approach to forecast the measurements of the DVL while it malfunctions. The current and past velocities obtained from SINS are taken as the predictor’s inputs. In this paper, we proposed a neural network-based approach to predict the body frame velocity when DVL is unavailable. Related methodologies in similar situations can be found in the literature on SINS/GNSS integrated navigation [20–22]. The main idea of these approaches is to build the map between SINS measurements (angular rate, specific force, velocity, position, and so forth) and GNSS measurements [21]. If the GNSS signals are available, the neural network is trained by the SINS and GNSS measurements. Once the outages of the GNSS happen, the virtual GNSS measurements can be obtained by the well trained neural network. Therefore, it is able to maintain the short-term stability of the SINS/GNSS integration. Inspired by these works, a nonlinear autoregressive exogenous (NARX) neural network model, which is able to forecast the velocity during the DVL malfunction, is constructed. The NARX neural network has been widely used in time series forecasting [23]. The prediction of the velocity can also be regarded as a time series forecasting problem. When DVL is available, the body frame velocity and its increment obtained from the SINS and DVL are collected to train the neural network. Once DVL is unavailable, the velocity forecasted by the well trained neural network is utilized to assist the SINS and hence maintain the accuracy of the integrated navigation.The rest of this paper is organized as follows. Section2 is devoted to the presentation of the SINS/DVL integrated navigation scheme. Both the SINS error dynamics model and the DVL error model are derived. Section 3 gives the algorithmic description of the neural network-based SINS/DVL integrated navigation scheme. In Section 4, the performance of the proposed algorithm is evaluated with ship-mounted experimental data collected in the Yangtze River. Conclusions are drawn in Section 5.


## 2. SINS/DVL Integrated Navigation

Figure1 shows the structure of the SINS/DVL integration. Normally, the SINS is consisted of three orthogonal gyroscopes and three orthogonal accelerometers, which are able to provide angular rate and specific force in the SINS body frame (denoted as b). With these measurements, the navigation solutions including position, attitude, and velocity can be obtained. The DVL provides velocity in the Doppler instrumental frame (denoted as d). To match the velocity of SINS, firstly, it should be transformed into the body frame with alignment calibration parameters. Then, the DVL velocity can be transformed into the navigation frame (denoted as n, local-level frame, and its orientation is north-east-sown (NED)) with the attitude of the SINS. As a velocity matching integration scheme, the velocities of the DVL and SINS in the navigation frame are chosen as the input of the Kalman Filter. With the estimation of the Kalman Filter, the navigation solutions can be reset and the sensor errors such as gyro bias and accelerometer bias can be corrected. As can be seen from Figure 1, with a feedback scheme, the navigation errors of the SINS, such as attitude error and velocity error, are compensating each Kalman filter cycle.Figure 1
SINS/DVL integrated navigation structure.


### 2.1. SINS Error Dynamics Model

Due to the inherent biases (gyro bias and accelerometer bias) of the SINS, the position error, attitude error, and the velocity error accumulate with time. It is known to us that, in the case of velocity matching integrated navigation, the position error is unobservable. Therefore, the position error is abandoned to be chosen as a state of the integration. The velocity and attitude error propagation process of the SINS can be described as follows [7]:(1)δv˙n=fn×ϕ−2ωien+ωenn×δvn+Cbn∇,(2)ϕ˙=−ωien+ωenn×ϕ+δωien+δωenn−Cbnε,where the subscript n denotes the components described in the navigation frame. δvn is the velocity error. ϕ is the attitude error. fn is the specific force in the navigation frame. Cbn is the direction cosine matrix of the body frame to the navigation frame. ωien denotes the angular rate of the Earth frame e relative to the inertial frame i. ωenn is the angular rate of the navigation frame relative to the Earth frame. ∇ and ε are the biases of the gyro and the accelerometer in the body frame, respectively. In SINS/DVL integration, ∇ and ε are usually modeled as random constants:(3)∇˙=0,(4)ε˙=0.The error states of the SINS are chosen as follows:(5)x=δvNδvEδvDϕNϕEϕD∇x∇y∇zεxεyεz.The SINS error dynamics model can be expressed as follows:(6)x˙=Fx+w,where w is a zeros-mean Gaussian white noise which is determined by the accuracy of the gyros and accelerometers. F is the state transformation matrix constructed according to equations (1)–(4). It can be given as follows:(7)F=F11F12Cbn03×3F21F2203×3−Cbn03×303×303×303×303×303×303×303×3,where(8)F11=vDRN+h−2ωiesinL−2vEtgLRE+hvNRN+h2ωiesinL+2vEtgLRE+hvD+vNtgLRE+h2ωiecosL+vERE+h−2vNRN+h−2ωiecosL−vERE+h0,whereRE and RN are the transverse radius and meridian radius of the Earth, respectively. L is the latitude. h denotes the altitude. ωie is the Earth’s rotation rate.vN, vE, and vD are the velocity in the north, east, and down direction, respectively.(9)F12=0−fDfEfD0−fN−fEfN0,where fN, fE, and fD are the specific force in the navigation frame. Also,(10)F21=01RE+h0−1RN+h000tgLRE+h0,(11)F22=0−ωiesinL−VEtgLRE+hVNRN+hωiesinL+VEtgLRE+h0ωiecosL+VERE+h−VNRN+h−ωiecosL−VERE+h0.


### 2.2. DVL Error Model

The velocity of DVL can be transformed into the navigation frame as follows:(12)v˜dn=C˜bnCdbvd,where vd is the velocity of DVL in the Doppler instrumental frame d. Cdb is the alignment matrix which presents the transformation of the Doppler instrumental frame to the body frame b; it can be presented as follows:(13)Cdb=I3×3−θ×,where I3×3 is a 3 × 3 identity matrix and θ× denotes the skew matrix of the misalignments between the DVL and the SINS. It can be obtained by calibration [7, 8]. C˜bn is the direction cosine matrix in error; it can be obtained by(14)C˜bn=I3×3−ϕ×Cbn,where ϕ× denotes the skew matrix of the attitude error ϕ. Substituting (14) into (12), it yields(15)v˜dn=I3×3−ϕ×CbnCdbvd,=CbnCdbvd+CbnCdbvd×ϕ,=vn+δvd.The velocity of the SINS in error can be modeled as(16)v˜SINSn=vn+δvn.Differencing the velocity of the SINS and DVL in the navigation frame, there exists(17)v˜SINSn−v˜dn=vn+δvn−vn+δvdn=δvn−CbnCdbvd×ϕ.It can be represented by the following equation:(18)z=v˜SINSn−v˜dn=Hx+η,where η is a zeros-mean Gaussian white noise which is determined by the accuracy of the DVL. H can be obtained from equation (17) as follows:(19)H=I3×3CbnCdbvd×03×6.


### 2.3. Standard Kalman Filter

The integrated navigation model described by equation (6) and equation (18) can be discretized as follows:(20)Xk=Φk,k−1Xk−1+Wk,Zk=HkXk−1+Vk,where Xk is the state vector, Zk is the measurement vector, Φk,k−1 is the state transition matrix, and Hk is the measurement matrix. Wk and Vk are uncorrelated zeros-mean Gaussian white noise and their conversances can be given as follows:(21)EWkWi=Qkk=i,0k≠i,(22)EVkVi=Rkk=i,0k≠i,(23)EVkWi=0,∀k,i.Kalman filter is able to estimate the state vector from the measurement vector in an optimum way. It is consisted of time update and measurement update. If there are no DVL measurements, time update is employed to predict the state vector as follows [11]:(24)X^k,k−1=Φk,k−1X^k−1,(25)Pk,k−1=Φk,k−1Pk−1Φk,k−1T+Qk−1,where X^k,k−1 is the predicted state vector and Pk,k−1 is the predicted covariance matrix of X^k,k−1. Once the DVL measurement is available, the measurement update can be accomplished as follows:(26)X^k=X^k,k−1+KkZk−HkX^k,k−1,(27)Kk=Pk,k−1HkTHkPk,k−1HkT+Rk−1,(28)Pk=I−KkHkPk,k−1I−KkHkT+KkRkKkT,where Kk is the Kalman Filter gain. Then, the navigation solutions of the SINS/DVL integration can be updated by the estimation of the state vector X^k.


## 2.1. SINS Error Dynamics Model

Due to the inherent biases (gyro bias and accelerometer bias) of the SINS, the position error, attitude error, and the velocity error accumulate with time. It is known to us that, in the case of velocity matching integrated navigation, the position error is unobservable. Therefore, the position error is abandoned to be chosen as a state of the integration. The velocity and attitude error propagation process of the SINS can be described as follows [7]:(1)δv˙n=fn×ϕ−2ωien+ωenn×δvn+Cbn∇,(2)ϕ˙=−ωien+ωenn×ϕ+δωien+δωenn−Cbnε,where the subscript n denotes the components described in the navigation frame. δvn is the velocity error. ϕ is the attitude error. fn is the specific force in the navigation frame. Cbn is the direction cosine matrix of the body frame to the navigation frame. ωien denotes the angular rate of the Earth frame e relative to the inertial frame i. ωenn is the angular rate of the navigation frame relative to the Earth frame. ∇ and ε are the biases of the gyro and the accelerometer in the body frame, respectively. In SINS/DVL integration, ∇ and ε are usually modeled as random constants:(3)∇˙=0,(4)ε˙=0.The error states of the SINS are chosen as follows:(5)x=δvNδvEδvDϕNϕEϕD∇x∇y∇zεxεyεz.The SINS error dynamics model can be expressed as follows:(6)x˙=Fx+w,where w is a zeros-mean Gaussian white noise which is determined by the accuracy of the gyros and accelerometers. F is the state transformation matrix constructed according to equations (1)–(4). It can be given as follows:(7)F=F11F12Cbn03×3F21F2203×3−Cbn03×303×303×303×303×303×303×303×3,where(8)F11=vDRN+h−2ωiesinL−2vEtgLRE+hvNRN+h2ωiesinL+2vEtgLRE+hvD+vNtgLRE+h2ωiecosL+vERE+h−2vNRN+h−2ωiecosL−vERE+h0,whereRE and RN are the transverse radius and meridian radius of the Earth, respectively. L is the latitude. h denotes the altitude. ωie is the Earth’s rotation rate.vN, vE, and vD are the velocity in the north, east, and down direction, respectively.(9)F12=0−fDfEfD0−fN−fEfN0,where fN, fE, and fD are the specific force in the navigation frame. Also,(10)F21=01RE+h0−1RN+h000tgLRE+h0,(11)F22=0−ωiesinL−VEtgLRE+hVNRN+hωiesinL+VEtgLRE+h0ωiecosL+VERE+h−VNRN+h−ωiecosL−VERE+h0.


## 2.2. DVL Error Model

The velocity of DVL can be transformed into the navigation frame as follows:(12)v˜dn=C˜bnCdbvd,where vd is the velocity of DVL in the Doppler instrumental frame d. Cdb is the alignment matrix which presents the transformation of the Doppler instrumental frame to the body frame b; it can be presented as follows:(13)Cdb=I3×3−θ×,where I3×3 is a 3 × 3 identity matrix and θ× denotes the skew matrix of the misalignments between the DVL and the SINS. It can be obtained by calibration [7, 8]. C˜bn is the direction cosine matrix in error; it can be obtained by(14)C˜bn=I3×3−ϕ×Cbn,where ϕ× denotes the skew matrix of the attitude error ϕ. Substituting (14) into (12), it yields(15)v˜dn=I3×3−ϕ×CbnCdbvd,=CbnCdbvd+CbnCdbvd×ϕ,=vn+δvd.The velocity of the SINS in error can be modeled as(16)v˜SINSn=vn+δvn.Differencing the velocity of the SINS and DVL in the navigation frame, there exists(17)v˜SINSn−v˜dn=vn+δvn−vn+δvdn=δvn−CbnCdbvd×ϕ.It can be represented by the following equation:(18)z=v˜SINSn−v˜dn=Hx+η,where η is a zeros-mean Gaussian white noise which is determined by the accuracy of the DVL. H can be obtained from equation (17) as follows:(19)H=I3×3CbnCdbvd×03×6.


## 2.3. Standard Kalman Filter

The integrated navigation model described by equation (6) and equation (18) can be discretized as follows:(20)Xk=Φk,k−1Xk−1+Wk,Zk=HkXk−1+Vk,where Xk is the state vector, Zk is the measurement vector, Φk,k−1 is the state transition matrix, and Hk is the measurement matrix. Wk and Vk are uncorrelated zeros-mean Gaussian white noise and their conversances can be given as follows:(21)EWkWi=Qkk=i,0k≠i,(22)EVkVi=Rkk=i,0k≠i,(23)EVkWi=0,∀k,i.Kalman filter is able to estimate the state vector from the measurement vector in an optimum way. It is consisted of time update and measurement update. If there are no DVL measurements, time update is employed to predict the state vector as follows [11]:(24)X^k,k−1=Φk,k−1X^k−1,(25)Pk,k−1=Φk,k−1Pk−1Φk,k−1T+Qk−1,where X^k,k−1 is the predicted state vector and Pk,k−1 is the predicted covariance matrix of X^k,k−1. Once the DVL measurement is available, the measurement update can be accomplished as follows:(26)X^k=X^k,k−1+KkZk−HkX^k,k−1,(27)Kk=Pk,k−1HkTHkPk,k−1HkT+Rk−1,(28)Pk=I−KkHkPk,k−1I−KkHkT+KkRkKkT,where Kk is the Kalman Filter gain. Then, the navigation solutions of the SINS/DVL integration can be updated by the estimation of the state vector X^k.


## 3. Neural Network-Based Integrated Navigation Structure

As mentioned in Section1, the DVL may fail to provide velocity in some situations. To deal with this problem, a neural network-based approach is proposed. The main idea is to forecast the velocity measurements by neural network during DVL malfunction. And hence the subsequent integrated navigation can be conducted with the predictions. Since the velocity of the DVL is in the Doppler instrumental frame d, it should be transformed into the body frame by the alignment matrix Cdb before integration as follows:(29)vb=Cdbvd.The neural network will predict the body frame velocity directly. In this paper, a nonlinear autoregressive exogenous neural network is employed [24]. That is, the current value of a time series can be forecasted by two series: the previous values of the same series and the current and previous values of the driving series. The driving series is the series that influences the series of interest.The NARX model can be described as follows [25]:(30)yk+1=Mykyk−1⋯yk−mxk+1xkxk−1⋯xk−m,where M⋅ is the mapping function of the neural network, xk is the value of the driving series at time k, and yk is the value of the target series at time k. Obviously, the body frame velocity sequence is the target time series. Considering that the body frame velocity increment sequence of SINS can also indicate the change of the velocity, it is chosen as the driving series. The velocity increment of the SINS in n-frame un can be obtained by the two-sample iteration algorithm [26]. The velocity increment of the SINS in b frame during each DVL update cycle can be given as follows:(31)Δvkb=∑i=1NCnbtk−1+i×Tuntk−1+i×T,where T is the SINS update cycle and N denotes the amount of SINS update during each DVL update cycle.The variables of the mapping function, which are initially stochastic, can be fine-tuned in the training process. The multilayer perceptron network is employed to perform the approximation and its configuration is shown in Figure2. Considering that the training of the neural network requires a lot of data, a light-weight neural network model is employed. Therefore, the employed model is easy for training and fine-tuning, and no massive training data is required. The network is composed of three layers: input layer, hidden layer, and output layer. Both the body frame velocity and the velocity increment have three dimensions, so there are six attributes of the input. The velocities of the previous two steps are also adopted as the input of the network. There are ten neurons in the hidden layer. The final output of the network is the predicted body frame velocity which is a three-dimensional vector. The Levenberg–Marquardt (LM) optimization method is adopted as the training function for the network [27].Figure 2
NARX generated by MATLAB R2014a.The structure of the improved SINS/DVL integration is shown in Figure3. When the DVL is available, the SINS is integrated with the DVL to get navigation solutions. Meanwhile, the neural network is trained by the velocity and velocity increment in b frame. The driving series can be obtained continuously by the SINS:(32)xk=Δvkb,k=1,2,⋯,m,where the velocity increment Δvkb can be obtained from equation (31). The target series can be acquired from equation (29) with DVL measurements as follows:(33)yk=vkb,k=1,2,⋯,m.Figure 3
Structure of the improved SINS/DVL integration.Once the DVL fails, the velocity inb frame can be predicted by the well trained network. However, with the DVL measurements, the network is able to predict only one step ahead. Therefore, the subsequent integrated navigation is conducted as follows:Step 1: predict the velocity inb frame one step ahead with the input time series of current and the previous two steps.Step 2: update the SINS navigation solutions and the velocity increment inb frame with the SINS raw data.Step 3: conduct the SINS/DVL integrated navigation and update navigation solutions. Update the driving series with the velocity increment obtained by Step 2. Update the target series with the prediction obtained by Step 1.Step 4: go to Step 1 until the integrated navigation is finished


## 4. Experimental Results and Discussion

### 4.1. Test Configuration

The ship-mounted experimental data were collected to evaluate the performance of the proposed algorithm. The trial was carried out in the Yangtze River. The equipped instruments include a navigation grade SINS, a bottom-locked DVL, and a NovAtel GPS receiver. The specifications of the SINS and DVL are shown in Tables2 and 3, respectively.Table 2
SINS specifications.
Parameter itemGyroscopeAccelerometerBias<0.02°/h(1σ)<5×10−5g (1σ)Update rate200 Hz200 HzBias stability<30 ppm<50 ppmDynamic range±200°(s)±15 gTable 3
DVL specifications.
Parameter itemVelocity accuracy±0.5%V ± 0.5 cm/sUpdate rate1 HzOperating rate300 kHzBottom-locked range300 mDynamic range−10 knot∼20 knot


### 4.2. Performance Evaluation of the SINS/DVL Integration

During the test, the ship sailed up to about 30 kilometers at the speed of around 9 knots (approximately 6600 s). From the experimental data, it is shown that the GPS receiver was able to provide credible position and velocity measurements during the whole test. Therefore, the integrated navigation results, including position, velocity, and attitude from SINS/GPS, can be used as the benchmark to compare with the SINS/DVL integration. Before integrated navigation, an initial alignment of SINS was conducted. The trajectories obtained from SINS/GPS and SINS/DVL are shown in Figure4. Figure 5 shows the changing of attitude. Figures 6 and 7 show the velocities in the navigation frame and Doppler instrumental frame, respectively. As can be seen from the figures, the roll and the pitch of the ship remain around −3° and 1.7°, respectively. The heading and the velocity of the ship vary slowly. The AUVs usually operate within a low dynamics range. It may fit the real motion of the AUVs, such as submarines. As can be seen from Figure 4, the two trajectories closely match each other. The error curve of the position is shown in Figure 8. And the final position error of the SINS/DVL integration is about 28 meters, which is less than 1% of the distance travelled. Predictably, as long as external position observations are unavailable, the position error will accumulate with time.Figure 4
Trajectories obtained from the SINS/GPS and the SINS/DVL.Figure 5
The attitude of the ship.Figure 6
The velocity of the ship in the navigation frame.Figure 7
The DVL measurements during the experiment.Figure 8
Position error of the SINS/DVL.As the DVL provides the velocity measurements in the Doppler instrumental frame but not geodetic frame, it leads to the slow convergence of the heading error and INS measurement errors (the gyro biases and the accelerometer biases). In addition, the AUVs usually operate within a low dynamics range, which makes this problem more serious. Both the gyro and the accelerometer biases in the up direction cannot be estimated as reliable. Therefore, the open loop is adopted to estimate the INS biases [28]. Misalignments of the SINS/DVL are shown in Figure 9. The misalignments converge with time. However, the heading error converged slower than the roll error and the pitch error. It oscillates at the beginning and then converges. From the partial magnification of Figure 9, the heading error remains around 0.01° finally. It is known that DVL provides velocity measurements in the Doppler instrumental frame. And it leads to the slow convergence of the heading. Figure 10 shows the velocity error in the north and east direction, respectively. As a velocity-aided integration, the velocity errors of SINS/DVL show fast convergence.Figure 9
Misalignments of the SINS/DVL.Figure 10
Velocity errors of SINS/DVL in the navigation frame.


### 4.3. Validation of the Proposed Neural Network-Based Algorithm

A test was designed to evaluate the performance of the proposed neural network-based algorithm. In practical use, the flag denoting whether the DVL is available has been set. As the DVL is available during the whole mission, it is assumed that DVL is unavailable after 4000 s. And the former data was employed to train the neural network. Therefore, the network is able to forecast the body frame velocity which can be used in the subsequent integrated navigation.The body frame velocity obtained by DVL can be regarded as the actual value. Figure11 compares the body frame velocity from the DVL and the network. As can be seen from the figure, the predicted values match well with the real value at the beginning, especially the first 200 s–300 s. However, with the increase of time, the difference of the velocities becomes larger.Figure 11
Body frame velocity obtained from the DVL and the neural network.Compared with the experimental results that DVLs are always available, Figures12 and 13 show the velocity errors and the position errors of the integrated navigation, respectively. It is shown in Figure 12 that the velocity error of the SINS/DVL with DVL measurements remains around zero. And the velocity error of the SINS/DVL with the predictions also remains around zero at the beginning. However, it diverges with the increase of time. Obviously, the divergence of the velocity error will lead to the growth of the position error. As can be seen from the partial magnification of Figure 13, the positioning error of the SINS/DVL with predictions is extremely close to that with DVL measurements during the first 200 s–300 s and then increases with time. From the experimental results presented above, it is clearly shown that the proposed neural network-based approach is able to deal with short-term (approximately 200 s–300 s) malfunction of the DVL. However, as the predicting error of the neural network becomes larger, the positioning error of SINS/DVL will increase gradually.Figure 12
Velocity errors of SINS/DVL in the navigation frame.Figure 13
Position errors of the SINS/DVL.Figure14 shows the attitude errors of the SINS/DVL. As can be seen from the figure, the influence of the inaccurate velocity predictions on the attitude is not that obvious. The error curves still match well with each other. The final heading error of the SINS integrated with the predictions is around 0.01°. However, it is expected that the difference of the attitude errors will become larger if a low accuracy SINS is employed.Figure 14
Attitude errors of the SINS/DVL.In practical use, when the DVL output is unavailable, the SINS work solely. A comparison has been done by comparing the position error of pure inertial navigation and SINS integrated with DVL predictions. It is clearly shown in Figure15 that the SINS/DVL integration with DVL predictions is able to reduce the error growth while the position error of the pure inertial navigation increases rapidly. This provides another confirmation to the superiority of the proposed method.Figure 15
Comparison of the position errors.Experiments have also been done by intentionally reducing the amount of the training data. Figure16 shows the position error of the SINS/DVL with 1000s training data. From partial magnification of the figure, it is found that the SINS/DVL integration is able to maintain accuracy for only about 100 s–150 s. It is shown that, once the amount of the training data is reduced, the accuracy of the predictions will be reduced, too.Figure 16
Position error of the SINS/DVL with 1000 s training data.


## 4.1. Test Configuration

The ship-mounted experimental data were collected to evaluate the performance of the proposed algorithm. The trial was carried out in the Yangtze River. The equipped instruments include a navigation grade SINS, a bottom-locked DVL, and a NovAtel GPS receiver. The specifications of the SINS and DVL are shown in Tables2 and 3, respectively.Table 2
SINS specifications.
Parameter itemGyroscopeAccelerometerBias<0.02°/h(1σ)<5×10−5g (1σ)Update rate200 Hz200 HzBias stability<30 ppm<50 ppmDynamic range±200°(s)±15 gTable 3
DVL specifications.
Parameter itemVelocity accuracy±0.5%V ± 0.5 cm/sUpdate rate1 HzOperating rate300 kHzBottom-locked range300 mDynamic range−10 knot∼20 knot


## 4.2. Performance Evaluation of the SINS/DVL Integration

During the test, the ship sailed up to about 30 kilometers at the speed of around 9 knots (approximately 6600 s). From the experimental data, it is shown that the GPS receiver was able to provide credible position and velocity measurements during the whole test. Therefore, the integrated navigation results, including position, velocity, and attitude from SINS/GPS, can be used as the benchmark to compare with the SINS/DVL integration. Before integrated navigation, an initial alignment of SINS was conducted. The trajectories obtained from SINS/GPS and SINS/DVL are shown in Figure4. Figure 5 shows the changing of attitude. Figures 6 and 7 show the velocities in the navigation frame and Doppler instrumental frame, respectively. As can be seen from the figures, the roll and the pitch of the ship remain around −3° and 1.7°, respectively. The heading and the velocity of the ship vary slowly. The AUVs usually operate within a low dynamics range. It may fit the real motion of the AUVs, such as submarines. As can be seen from Figure 4, the two trajectories closely match each other. The error curve of the position is shown in Figure 8. And the final position error of the SINS/DVL integration is about 28 meters, which is less than 1% of the distance travelled. Predictably, as long as external position observations are unavailable, the position error will accumulate with time.Figure 4
Trajectories obtained from the SINS/GPS and the SINS/DVL.Figure 5
The attitude of the ship.Figure 6
The velocity of the ship in the navigation frame.Figure 7
The DVL measurements during the experiment.Figure 8
Position error of the SINS/DVL.As the DVL provides the velocity measurements in the Doppler instrumental frame but not geodetic frame, it leads to the slow convergence of the heading error and INS measurement errors (the gyro biases and the accelerometer biases). In addition, the AUVs usually operate within a low dynamics range, which makes this problem more serious. Both the gyro and the accelerometer biases in the up direction cannot be estimated as reliable. Therefore, the open loop is adopted to estimate the INS biases [28]. Misalignments of the SINS/DVL are shown in Figure 9. The misalignments converge with time. However, the heading error converged slower than the roll error and the pitch error. It oscillates at the beginning and then converges. From the partial magnification of Figure 9, the heading error remains around 0.01° finally. It is known that DVL provides velocity measurements in the Doppler instrumental frame. And it leads to the slow convergence of the heading. Figure 10 shows the velocity error in the north and east direction, respectively. As a velocity-aided integration, the velocity errors of SINS/DVL show fast convergence.Figure 9
Misalignments of the SINS/DVL.Figure 10
Velocity errors of SINS/DVL in the navigation frame.


## 4.3. Validation of the Proposed Neural Network-Based Algorithm

A test was designed to evaluate the performance of the proposed neural network-based algorithm. In practical use, the flag denoting whether the DVL is available has been set. As the DVL is available during the whole mission, it is assumed that DVL is unavailable after 4000 s. And the former data was employed to train the neural network. Therefore, the network is able to forecast the body frame velocity which can be used in the subsequent integrated navigation.The body frame velocity obtained by DVL can be regarded as the actual value. Figure11 compares the body frame velocity from the DVL and the network. As can be seen from the figure, the predicted values match well with the real value at the beginning, especially the first 200 s–300 s. However, with the increase of time, the difference of the velocities becomes larger.Figure 11
Body frame velocity obtained from the DVL and the neural network.Compared with the experimental results that DVLs are always available, Figures12 and 13 show the velocity errors and the position errors of the integrated navigation, respectively. It is shown in Figure 12 that the velocity error of the SINS/DVL with DVL measurements remains around zero. And the velocity error of the SINS/DVL with the predictions also remains around zero at the beginning. However, it diverges with the increase of time. Obviously, the divergence of the velocity error will lead to the growth of the position error. As can be seen from the partial magnification of Figure 13, the positioning error of the SINS/DVL with predictions is extremely close to that with DVL measurements during the first 200 s–300 s and then increases with time. From the experimental results presented above, it is clearly shown that the proposed neural network-based approach is able to deal with short-term (approximately 200 s–300 s) malfunction of the DVL. However, as the predicting error of the neural network becomes larger, the positioning error of SINS/DVL will increase gradually.Figure 12
Velocity errors of SINS/DVL in the navigation frame.Figure 13
Position errors of the SINS/DVL.Figure14 shows the attitude errors of the SINS/DVL. As can be seen from the figure, the influence of the inaccurate velocity predictions on the attitude is not that obvious. The error curves still match well with each other. The final heading error of the SINS integrated with the predictions is around 0.01°. However, it is expected that the difference of the attitude errors will become larger if a low accuracy SINS is employed.Figure 14
Attitude errors of the SINS/DVL.In practical use, when the DVL output is unavailable, the SINS work solely. A comparison has been done by comparing the position error of pure inertial navigation and SINS integrated with DVL predictions. It is clearly shown in Figure15 that the SINS/DVL integration with DVL predictions is able to reduce the error growth while the position error of the pure inertial navigation increases rapidly. This provides another confirmation to the superiority of the proposed method.Figure 15
Comparison of the position errors.Experiments have also been done by intentionally reducing the amount of the training data. Figure16 shows the position error of the SINS/DVL with 1000s training data. From partial magnification of the figure, it is found that the SINS/DVL integration is able to maintain accuracy for only about 100 s–150 s. It is shown that, once the amount of the training data is reduced, the accuracy of the predictions will be reduced, too.Figure 16
Position error of the SINS/DVL with 1000 s training data.


## 5. Conclusions

To deal with the problem of DVL malfunction in SINS/DVL integrated navigation, a neural network-based approach is proposed. When the DVL is available, the measurements from the SINS and DVL are employed to train the network. Once the DVL fails, the well trained network is able to forecast the velocity which can be used in the subsequent integrated navigation. From the experimental results, the following conclusions can be drawn.(1)
With a navigation grade SINS and a DVL, the trained neural network is able to provide credible velocity predictions. But the error of the prediction will increase with time gradually.(2)
With the predicted velocity series from the well trained network, the SINS/DVL integration is able to maintain accuracy for about 200 s–300 s. Therefore, the proposed approach is capable of dealing with DVL short-term malfunction.(3)
If the amount of training data is reduced, the accuracy of DVL predictions may decrease, too.In this paper, a navigation grade SINS is employed in the experiment. Further investigation is still needed to determine whether this approach is suitable for low cost inertial navigation systems.



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*Source: 2891572-2020-07-26.xml*