Application of adaptive Kalman filter in rocket impact point estimation

YAN Xiao-long, CHEN Guo-guang, BAI Dun-zhuo

(1. College of Mechatronic Engineering, North University of China, Taiyuan 030051, China;2. Yuxi Industries Group Co.,Ltd., Nanyang 473000, China)

閆小龍1， 陳國光1， 白敦卓2

(1. 中北大學(xué) 機(jī)電工程學(xué)院， 山西 太原 030051； 2. 豫西工業(yè)集團(tuán)有限公司， 河南 南陽 473000)

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Application of adaptive Kalman filter in rocket impact point estimation

YAN Xiao-long1, CHEN Guo-guang1, BAI Dun-zhuo2

(1.CollegeofMechatronicEngineering,NorthUniversityofChina,Taiyuan030051,China;2.YuxiIndustriesGroupCo.,Ltd.,Nanyang473000,China)

In order to measure the parameters of flight rocket by using radar, rocket impact point was estimated accurately for rocket trajectory correction. The Kalman filter with adaptive filter gain matrix was adopted. According to the particle trajectory model, the adaptive Kalman filter trajectory model was constructed for removing and filtering the outliers of the parameters during a section of flight detected by three-dimensional data radar and the rocket impact point was extrapolated. The results of numerical simulation show that the outliers and noise in trajectory measurement signal can be removed effectively by using the adaptive Kalman filter and the filter variance can converge in a short period of time. Based on the relation of filtering time and impact point estimation error, choosing the filtering time of 8-10 s can get the minimum estimation error of impact point.

rocket; adaptive Kalman filter; outliers; impact point estimation

0 Introduction

With the increasing requirements for rocket firing accuracy, rockets must be corrected in the process of flight by estimating the rocket flight status and predicting the impact point based on the observation data of flight rocket from radar, global positioning system (GPS), etc., then comparing the impact point with the target and calculating the error, finally correcting rockets trajectory according to the error.

In this paper, we get rocket flight trajectory by means of three-dimensional data radar. Because of big radar errors in fight process, which impacts the data for impact point estimation of the rocket, radar signal noise must be filtered out for getting correct trajectory data, including random noise in actual probing radar, the noises called “outliers” from the actual noise with big errors, which have a big impact on filtering algorithm and affect the accuracy of the results. Therefore, Kalman filter algorithm with outliers removing is proposed in this paper, which improves the accuracy of rocket impact point estimation effectively[1].

1 Rocket exterior trajectory filtering and extrapolation model

After getting the radar measurement data, according to the ballistic trajectory model, the measured and extrapolated placement is filtered, then data error is fed back in time, finally the rocket trajectory is corrected using rocket actuator. Because rocket trajectory corredtion needs to calculate and estimate the impact point in time and accurately, we select the particle trajectory model with high-speed calculation to meet the requirement of high-speed and high-accuracy calculation. The model is written

(1)

Wesetx1, x2, x3, x4, x5, x6, x7, x8, x9andx10asstatevariablesofKalmanfilter,thusthereis

whereCbis the projectile motion, and it can be set at zero[2];εx,εyandεzare the positioning errors.

Then we can get the system state equation as

(2)

where W(k)iszero-meanrandomnoiseinterference.

2 Filtering measurement equation

Based on the measurement results with Slant ranger, azimuth angleβand elevation angleεby means of three-dimensional data radar, we can obtain the relation between the radar measurement value and the ground coordinate system as

(3)

where (xo,yo,zo) are the coordinate of the radar antenna center in the ground coordinate system[3].

The coordinate radar measurement array isz=(r，β，ε). Vkisradarmeasurementnoise.AssumethatVkiszero-meanGaussianwhitenoise,andthediscreteformofthemeasurementnoisecovariancematrixisgivenby

(4)

Inthecourseofrocketlaunching,radarcoordinatesystemisnotjusttheemplacementcoordinate.Therefore,weneedtoconvertthetwocoordinatesystems[4],andtheconversionrelationis

(5)

whereεX,εYandεZarethreerotationanglesofthethree-dimensionalspacerectangularcoordinatewhentransformation; R1(εX), R2(εY)andR3(εZ)arecorrespondingrotationmatrices;andR0is expressed as

Measurement equation can be obtained as

(6)

3 Kalman filter

Kalman filter equations are divided into two parts: one is Kalman filter equation, which is responsible for the estimated path forward of the state; the other is Kalman filter gain matrix recurrence equation, which is responsible for feedback priori estimation and correction for the prediction[5]. The discrete Kalman optimal estimation equations are as follows:

1) Optimal prediction estimation equation

(7)

2) Optimal filtering estimation equation

(8)

3) Optimal filter gain matrix equation

(9)

4) Optimal prediction estimation error variance matrix

(10)

5) Optimal filtering estimation error variance matrix equation

(11)

The statistical propertiesE{X(0)} andP(0) of state vector X(0)areknownatt0.Inordertoobtainunbiasedestimates,weset

4 Identification and treatment of outliers

Actually measured signals must go through transmission system, data acquisition system, conversion system and other systems, and then the target digital signals are sent to Kalman filter, which will not only have random noise, but also may generate some outliers with large difference compared with actual data by outside irregular interference. The existence of these outliers has great influence on the results of Kalman filter[6].

We set

(12)

(13)

In the above equations,Cis 3×1 dimensional vector which represents an allowable range of measured value error based on actual trajectory metrology tool, and it can be changed according to the precision settings with different measurement tools at different times[7]. By means of this identification method, we can determine which measured value of each component exceeds the limit error. Whenεkis not in allowable error range, we need to modify the predicted value, thus the optimal filtering estimation equation can be expressed as

(14)

whereM(k)=iK(k),i∈[0,1].

That is, changing the filter gain matrix equation can make filter gain change due to the presence of outliers. This makes optimal filter estimation equation correct, eliminates the negative filtering effect that brings outliers to measurement information. Absolutely, when the measured value does not exceed the allowable range and setsi=1, the filter gain matrix equation will not be changed.

5 Numerical simulation

Inordertotesttheactualfilteringeffectofthefilter,itisneededtodonumericalsimulationcalculation.Inthispaper,weselecttherocketwithfiringrangeof40kmastheexampleofthesimulation,using5Dtrajectorymodeltocalculatethetrajectoryrawdata,addingGaussianwhitenoisewithmeanofzerointotheradarnoise,andtakinglargeerrorswithinuncertainperiodasradarmeasurementsoutliersforformingthree-dimensionaldataradartomeasuredata[8].UsingKalmanfilterwithoutliertreatmenttodiscriminate,process,andfilteroutliersintheradarmeasureddata,trajectoryisextrapolatedusingparticleexteriortrajectoryequationandimpactpoint(X, Z)isestimated.Afterthesimulatedprojectilelaunchesfor2.5s,theradarbeginstotrackthetargetandthesamplingintervalis0.1s.Whenthesimulatedradarworksforabout45s,thetrajectorydatastarttobefiltered.Whencontinuousmonitoringtimeis70s,thefilteringprocessisover.Figs.1, 2and3aretheresultsofoutliersremovingandfilteringindifferentdirections.

Fig.1 Data processing on X axis

Fig.2 Data processing on Y axis

Fig.3 Data processing on Z axis

After getting the filtered and removed outliers, we select filtering results at the time 70 s and use the particle trajectory equation for rocket impact point (X,Z) estimation. By comparing the estimation to the actual trajectory, the impact point estimation error is got. Filter variances inX,YandZdirections are shown in Fig.4. It can be seen that the filter variance converge stabilizes quickly after 20 s.

Fig.4 Filter variances in X, Y and Z directions

Fig.5 shows the relation of filtering time and impact point estimation error which is extrapolated from the particle trajectory equation according to rocket flight data at the end of filtering. It can be seen that there is a close relation between the impact point estimation accuracy and filtering time. The impact point estimation accuracy increases with the increase of filtering time, but the accuracy increases slowly after a period of time[9]. It should be reasonable to select the time of radar tracking rocket and radar data filtering time, so that we can get high estimation accuracy of placement in a relatively short time.

The numerical simulation results show that for the 122 mm rocket, if the sampling time is 0.1 s, selecting radar tracking and filtering time for 8-10 s can get good results.

Fig.5 Relation of filtering time and impact point estimation error

6 Conclusion

In this paper, the rocket trajectory data measured by three-dimensional data radar with random noise signals were filtered based on Kalman filter with adaptive gain matrix according to presence of outliers, by using extrapolation particle trajectory equation to estimate impact point according to trajectory data after filter provides effective data for rocket correction. Numerical simulation was conducted using the generated trajectory data and the results show that when there are outliers and large random noise of radars, using the designed filter can get trajectory data which is close to the true value. In different times of radar tracking and filtering, the impact point estimation accuracy will be different. With the increas of radar tracking and filtering time, the impact point estimation accuracy increases continuously. But when the time increases to a certain level, the accuracy tends to be stable.

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自適應(yīng)卡爾曼濾波器在火箭彈落點(diǎn)估計中的應(yīng)用

利用雷達(dá)對火箭彈一段飛行過程中的參數(shù)進(jìn)行量測， 對火箭彈落點(diǎn)進(jìn)行了準(zhǔn)確估計， 實現(xiàn)了火箭彈的軌跡修正。采用具有自適應(yīng)調(diào)節(jié)濾波增益矩陣的卡爾曼濾波器， 結(jié)合質(zhì)點(diǎn)彈道模型， 建立了自適應(yīng)卡爾曼濾波彈道模型， 完成了對三坐標(biāo)雷達(dá)探測的一段火箭彈飛行參數(shù)的野值處理與濾波， 并對火箭彈落點(diǎn)進(jìn)行外推。 數(shù)值仿真結(jié)果表明， 經(jīng)自適應(yīng)調(diào)節(jié)的卡爾曼濾波器濾波后， 彈道量測信號中的野值與噪聲被有效去除， 且濾波方差可以在短時間內(nèi)收斂。 根據(jù)濾波時間與落點(diǎn)估計誤差的關(guān)系， 采用濾波時間為8-10 s方案， 可得到最佳的落點(diǎn)估計。

火箭彈； 自適應(yīng)卡爾曼濾波器； 野值； 落點(diǎn)估計

YAN Xiao-long, CHEN Guo-guang, BAI Dun-zhuo. Application of adaptive Kalman filter in rocket impact point estimation. Journal of Measurement Science and Instrumentation, 2015, 6(3)： 212-217.[

閆小龍1， 陳國光1， 白敦卓2

(1. 中北大學(xué) 機(jī)電工程學(xué)院， 山西 太原 030051； 2. 豫西工業(yè)集團(tuán)有限公司， 河南 南陽 473000)

10.3969/j.issn.1674-8042.2015.03.002]

YAN Xiao-long (13994230892@139.com)

1674-8042(2015)03-0212-06 doi： 10.3969/j.issn.1674-8042.2015.03.002

Received date： 2015-05-11

CLD number： TJ415 Document code： A