# Mathematical Model of Movement of the Observation and Tracking Head of an Unmanned Aerial Vehicle Performing Ground Target Search and Tracking

Authors: Izabela Krzysztofik; Zbigniew Koruba
Journal: Journal of Applied Mathematics
 (2014)

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## Abstract

The paper presents the kinematics of mutual movement of an unmanned aerial vehicle (UAV) and a ground target. The controlled observation and tracking head (OTH) is a device responsible for observing the ground, searching for a ground target, and tracking it. The preprogrammed movement of the UAV on the circle with the simultaneous movement of the head axis on Archimedes’ spiral during searching for a ground target, both fixed (bunkers, rocket missiles launching positions, etc.) and movable (tanks, infantry fighting vehicles, etc.), is considered. Dynamics of OTH during the performance of the above mentioned activities is examined. Some research results are presented in a graphical form.


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## Body

## 1. Introduction

Due to the advantages of unmanned aerial vehicles (UAV) in relation to manned aircrafts, the multitask UAVs have become the basic equipment of a modern army [1]. They can carry out various tasks, such as aerial and radiolocation reconnaissance, observation of the battlefield, radioelectronic fight, adjustment of the artillery fire, target identification, laser indication of the target, assessment of the effects of striking other types of weapons, and imitation of air targets. UAVs can also have a wide civilian application, for example, observation and control of pipelines, electric tractions and road traffic. Because of that, more than 250 UAV models are developed and manufactured all over the world [2]. Many scientific institutions are engaged in developing and identifying models of dynamics and flight control of UAVs. For instance, papers [3, 4] present the comprehensive research on modelling the dynamics of flight of K100 UAV and Thunder Tiger Raptor 50 V2 Helicopter, respectively. Mathematical models of UAV with 6 degrees of freedom (6-DoF) introduced on the basis of the Newton’s rules of dynamics were presented, whereas [5] presents the methodology of modelling the dynamics of UAV flight with the use of neural networks. Paper [6] presents the mathematical model and the experimental research on SUAVI. That vehicle can take off and land vertically. The model was carried out with the use of the Newton-Euler formalism. Moreover, the controllers for controlling the height and stabilizing the vehicle’s location have been developed. Paper [7] describes the problem of flight dynamics of the UAV formation with the use of models with 3 and 6 degrees of freedom.An operation of UAV during the completion of a task is a complex process requiring comprehensive technical means and systems. The control system of UAV is one of the most important systems. Its task is to measure, evaluate, and control flight parameters, as well as properly control the flight and observation systems. Thanks to the use of complex microprocessor systems, the comprehensive automation of the mentioned processes is possible. Formerly, during the completion of a mission it was necessary to maintain bilateral communications with the ground control point. In modern UAVs, autonomy plays an important role during detecting and tracking a ground target.Paper [8] presents the model of the UAV autopilot and its sensors in the Matlab-Simulink environment for simulation research. Papers [9–11] pertain to planning and optimizing the trajectory of movement of the vehicle. The aspects of designing PID controllers for the systems of UAV flight control have been discussed in papers [12, 13].From the quoted review of the literature it appears that the research mainly concentrates on UAV dynamics and control, without the consideration of the model of movement of the observation and tracking head (OTH) which is one of the most significant elements of the unmanned aerial vehicle. OTH is used for automatic searching for and tracking of targets intended for destruction [14]. This paper presents the mathematical model of kinematics of the movement of UAV, the ground target, and the dynamics of the controlled head located on the UAV deck. It needs to be emphasized that the problem of modelling, examining the dynamics, and control of such heads in the conditions of interferences from its base (deck of the manoeuvring UAV) is still topical. The paper examines this type of OTH with the built-in television and thermographic cameras and the laser illuminator.


## 2. Model of Movement Kinematics of UAV, OTH and Ground Target

General view of the process of searching for a target on the surface of the ground by OTH from UAV deck is shown in Figure1, whereas the operation algorithm of OTH during scanning the ground surface and tracking a target detected on it is shown in Figure 2.Figure 1
General view of the process of scanning the ground surface from UAV deck.Figure 2
Diagram of operation of OTH mounted on UAV deck.During the search for a ground target from UAV deck, the axis of OTH should perform the desired movements and circle strictly defined lines on the ground with the use of its extension. The optical system of OTH, having a certain viewing angle, may in this way encounter a light or infrared signal emitted by the moving object. Therefore, one should choose the kinematic parameters of mutual movement of UAV deck and OTH in such a way that the likelihood of detecting a target was the highest [15]. After locating a target, OTH goes to the tracking mode; that is, from that moment its axis has a specific location in space being pointed at the target.Figure3 shows the kinematics of mutual movement of the head axis and UAV during searching for a target on the ground surface. Individual coordinate systems have the following meaning:Oxgygzg—Earth-fixed reference system,Cxayaza—coordinate system connected with target observation line (TOL),Cxcyczc—movable coordinate system connected with UAV velocity vector.Figure 3
Kinematics of mutual movement of the head axis and UAV during scanning the ground surface.The velocity of changing vectorR→ in time, during searching for and tracking a target, is as follows:
(1)dR→dt=Π(to,td)·(V→c-V→h)+[Π(td,tt)+Π(tt,te)]·(V→c-V→t),
where R→ is vector of the mutual distance of points C and H (during scanning the space) or points C and T (during tracking); V→c,V→h,V→t are vectors of the velocity of movement of the centre of mass of UAV, of points H and T, respectively; Π(to,td), Π(td,tt), Π(tt,te) are functions of rectangular impulse; to is the moment the scanning the ground is started; td is the moment a target is detected; tt is the moment the tracking the target is started; te is the moment the scanning process and tracking the target is finished.We project the left side of (1) on the axes of the coordinate system Cxayaza (Figure 3) connected with vector R→. In the result we get
(2)dR→dt=dRdti→a+|i→aj→ak→aωRxaωRyaωRzaR00|=i→adRdt+j→aRdσdtcos⁡⁡ε-k→aRdεdt,
where ωRxa, ωRya, ωRza are components of angular velocity of TOL and σ, ε are angles of deflection and inclination of vector R→.Next, we project the right side of (1) (i.e., velocities V→c, V→h and V→t) on the axes of the system Cxayaza and get
(3)dRdt=Π(to,td)·(Vcxa-Vhxa)+[Π(td,tt)+Π(tt,te)]·(Vcxa-Vtxa),Rdσdtcos⁡ε=Π(to,td)·(Vcya-Vhya)+[Π(td,tt)+Π(tt,te)]·(Vcya-Vtya),Rdεdt=Π(to,td)·(Vcza-Vhza)+[Π(td,tt)+Π(tt,te)]·(Vcza-Vtza).Individual components of velocity vectorsV→c, V→h and V→t in the system Cxayaza are as follows:(4a)Vcxa=Vc[cos⁡⁡εcos⁡⁡γccos⁡⁡(σ-χc)+sin⁡εsin⁡γc],(4b)Vcya=-Vccos⁡⁡γcsin⁡(σ-χc),(4c)Vcza=Vc[sin⁡εcos⁡⁡γccos⁡⁡(σ-χc)-cos⁡⁡εsin⁡γc],(5a)
V
h
x
a
=
V
h
[
cos
⁡
⁡
ε
cos
⁡
⁡
γ
h
cos
⁡
⁡
(
σ
-
χ
h
)
+
sin
⁡
ε
sin
⁡
γ
h
]
,
(5b)
V
h
y
a
=
-
V
h
cos
⁡
⁡
γ
h
sin
⁡
(
σ
-
χ
h
)
,
(5c)
V
h
z
a
=
V
h
[
sin
⁡
ε
cos
⁡
⁡
γ
h
cos
⁡
⁡
(
σ
-
χ
h
)
-
cos
⁡
⁡
ε
sin
⁡
γ
h
]
,(6a)
V
t
x
a
=
V
t
[
cos
⁡
⁡
ε
cos
⁡
⁡
γ
t
cos
⁡
⁡
(
σ
-
χ
t
)
+
sin
⁡
ε
sin
⁡
γ
t
]
,
(6b)
V
t
y
a
=
-
V
t
cos
⁡
⁡
γ
t
sin
⁡
(
σ
-
χ
t
)
,
(6c)
V
t
z
a
=
V
t
[
sin
⁡
ε
cos
⁡
⁡
γ
t
cos
⁡
⁡
(
σ
-
χ
t
)
-
cos
⁡
⁡
ε
sin
⁡
γ
t
]
,
where χc, γc are UAV flight angles, χh, γh are angles of deflection and inclination of velocity vector of point H, and χt, γt are angles of deflection and inclination of velocity vector of point T.For the simplification of reasoning, we assume that the movement of UAV, during searching and tracking, is done on a horizontal plane at a set altitudeHc, whereas the target and point H move in the ground plane. Then, we can assume that
(7)γc=0,γt=0,γh=0.We mark that(8)r=Rcos⁡⁡εThe derivative of that expression in relation to time is as follows:(9)drdt=dRdtcos⁡⁡ε-Rdεdtsin⁡ε.Let us substitute (4a)–(6c) into (3). Next, taking into account (7)–(9), (3) will have the following form:
(10)drdt=Π(to,td)[Vccos⁡⁡(σ-χcs)-Vhcos⁡⁡(σ-χh)]+Π(td,tt)[Vccos⁡⁡(σ-χcd)-Vtcos⁡⁡(σ-χt)]+Π(tt,te)[Vccos⁡⁡(σ-χct)-Vtcos⁡⁡(σ-χt)],(11)dσdt=Π(to,td)Vcsin⁡(σ-χcs)-Vhsin⁡(σ-χh)r+Π(td,tt)·Vcsin⁡(σ-χcd)-Vtsin⁡(σ-χt)r+Π(tt,te)Vcsin⁡(σ-χct)-Vtsin⁡(σ-χt)r,
where r is mutual distance of points C and H (during scanning) or C and T (during tracking); χcs is angle of deflection of UAV velocity vector during scanning the ground by the head; χcd is angle of deflection of UAV velocity vector during the passage from preprogrammed flight to tracking flight; and χct is angle of deflection of UAV velocity vector during the flight tracking the detected target.We demand that, at the moment of detecting the target, UAV automatically is starting the passage to the flight tracking the detected target; that is, it is moving at a set constant distance from the targetrc0=Rc0cos⁡⁡ε=const (in a horizontal plane at a constant altitude Hc).If the mutual distancer of points C and T is different from rc0 then the angle of deflection of UAV velocity vector χc=χcd changes in accordance with the relationship:
(12)dχcddt=ac·sign⁡(rc0-r)dσdt,
where ac is the set constant of proportional navigation.After the fulfillment of the conditionr=rc0 the programme of angle change χct can be determined from (10):
(13)χct=σ-arccos⁡⁡[VtVccos⁡⁡(σ-χt)].The path of UAV flight during scanning and tracking is as follows:(14a)drcdt=Π(to,td)Vccos⁡⁡(θc-χcs)+Π(td,tt)Vccos⁡⁡(θc-χcd)drcdt=+Π(tt,te)Vccos⁡⁡(θc-χct),(14b)dθcdt=Π(to,td)Vcrcsin⁡(θc-χcs)+Π(td,tt)Vcrcsin⁡(θc-χcd)dθcdt=+Π(tt,te)Vcrcsin⁡(θc-χct),(15)rcx=rccos⁡⁡θc,rcy=rcsin⁡θc,
where rc is vector of location of UAV mass centre (point C) and θc is angle of deflection of vector rc.Path of movement of pointH is as follows:(16a)dRhdt=Π(to,td)Vhcos⁡⁡(θh-χh),(16b)dθhdt=Π(to,td)Vhsin⁡(θh-χh),(17)Rhx=Rhcos⁡⁡θh,Rhy=Rhsin⁡θh,
where Rh is vector of location of point H and θh is angle of deflection of vector Rh.Path of movement of the target is as follows:(18a)dRtdt=Π(td,te)Vtcos⁡⁡(θt-χt),(18b)dθtdt=Π(td,te)Vtsin⁡(θt-χt),(19)Rtx=Rtcos⁡⁡θt,Rty=Rtsin⁡θt,
where Rt is vector of location of point T and θt is angle of deflection of vector Rt.Desired anglesϑhr,ψhr and angular velocities ϑ˙hr,ψ˙hr of deflection of OTH axis can be determined from the following relationships:
(20)ϑhr=arctgrxHc,dϑhrdt=Hc(drx/dt)Hc2+(rx)2,ψhr=arctgryHc,dψhrdt=Hc(dry/dt)Hc2+(ry)2,
where
(21)rx=rcos⁡⁡σ,ry=rsin⁡σ;drxdt=drdtcos⁡⁡σ-rdσdtsin⁡σ;drydt=drdtsin⁡σ+rdσdtcos⁡⁡σ.Values (20) are used for determining the preprogrammed controls influencing the head.


### 2.1. Scanning the Ground Surface during UAV Flight on a Circle

We assume that during scanning the set area of the ground, UAV flight is at a constant altitudeHc in a horizontal plane on the circle of the set radius rc with constant velocity Vc (Figure 3).Then the preprogrammed UAV flight can be determined from the following relationships:(22)Vc=ωc·rc,χc=ωct.At the same time, we control the head axis in such a way that it drawn on the surface of the ground a curve in the shape of Archimedean spiral with angular velocity(23)ωh=2πVhρh.VelocityVh is to be chosen in such a way that OTH mounted on UAV deck could in the set time ts scan densely enough the set surface of the area in the shape of a circle of the radius Rs.If the angle of vision of the head’s optical system amounts toϕh then lens coverage embraces the surface similar in shape to a circle of the radius:
(24)ρh=12Hcϕh.After detecting a target at the momenttd, UAV passes into the tracking flight according to the relationship (12), while the target is lit with a laser beam for the period of time tl. Hence, the total time of the process of detecting, tracking, and lighting the target amounts to te=td+tl.


## 2.1. Scanning the Ground Surface during UAV Flight on a Circle

We assume that during scanning the set area of the ground, UAV flight is at a constant altitudeHc in a horizontal plane on the circle of the set radius rc with constant velocity Vc (Figure 3).Then the preprogrammed UAV flight can be determined from the following relationships:(22)Vc=ωc·rc,χc=ωct.At the same time, we control the head axis in such a way that it drawn on the surface of the ground a curve in the shape of Archimedean spiral with angular velocity(23)ωh=2πVhρh.VelocityVh is to be chosen in such a way that OTH mounted on UAV deck could in the set time ts scan densely enough the set surface of the area in the shape of a circle of the radius Rs.If the angle of vision of the head’s optical system amounts toϕh then lens coverage embraces the surface similar in shape to a circle of the radius:
(24)ρh=12Hcϕh.After detecting a target at the momenttd, UAV passes into the tracking flight according to the relationship (12), while the target is lit with a laser beam for the period of time tl. Hence, the total time of the process of detecting, tracking, and lighting the target amounts to te=td+tl.


## 3. The Model of Dynamics of the Controlled Observation and Tracking Head

A spatial model of dynamics of the head presented in Figure4 was adopted for the paper. OTH comprises two basic parts: external frame and internal frame with camera. Movement of the head is determined with the use of two angles: angle of head deflection ψh and angle of head inclination ϑh [16].Figure 4
General view of the observation and tracking head.The following coordinate systems, shown in Figure5, have been introduced:Cxdydzd—the movable system connected with the UAV deck,Ohxh1yh1zh1—the movable system connected with the external frame of the head,Ohxhyhzh—the movable system connected with internal the frame of the head (including camera).Figure 5
Transformations of the coordinate systems.Components of angular velocity of the external frame of the head are(25a)ωxh1=pc*cos⁡⁡ψh+qc*sin⁡ψh,(25b)ωyh1=-pc*sin⁡ψh+qc*cos⁡⁡ψh,(25c)ωzh1=ψ˙h+rc*,where pc*,qc*,rc* are components of angular velocity of UAV.Components of angular velocity of the internal frame of the head are(26a)ωxh=ωxh1cos⁡⁡ϑh-ωzh1sin⁡ϑh,(26b)ωyh=ωyh1+ϑ˙h,(26c)ωzh=ωxh1sin⁡ϑh+ωzh1cos⁡⁡ϑh.Components of linear velocity of displacement of mass centre of the external frame of the head are(27a)Vxh1=Vccos⁡⁡ψh,(27b)Vyh1=-Vcsin⁡ψh,(27c)Vzh1=0.Components of linear velocity of displacement of mass centre of the internal frame of the head are(28a)Vxh=Vxh1cos⁡⁡ϑh+lhωyh1sin⁡ϑh,(28b)Vyh=Vyh1+lh(ωzh1+ωzh),(28c)Vzh=Vxh1sin⁡ϑh-lh(ωyh1cos⁡⁡ϑh+ωyh).Using the second order Lagrange equations, the following equations of the head movement have been derived:(29)Jzh1ddtωzh1-Jxhddt(ωxhsin⁡ϑh)+Jzhddt(ωzhcos⁡⁡ϑh)+mrwlhddt[Vyh(1+cos⁡⁡ϑh)]-(Jxh1-Jyh1)ωxh1ωyh1-Jxhωxhωyh1cos⁡⁡ϑh+Jyhωyhωxh1-Jzhωzhωyh1sin⁡ϑh+minlh[Vxhωxh1sin⁡ϑh-Vyhωyh1sin⁡ϑh-Vzhωxh1(1+cos⁡⁡ϑh)]+minlh[Vxh1(ωzh1+ωzh)+Vyh1ωyhsin⁡ϑh]=Mex+Mexg-Mdex,Jyhddtωyh-minlhddtVzh+(Jxh-Jzh)ωxhωzh-minlh[Vyhωxh-Vxhωyh]=Min+Ming-Mdin,
where ψh,ϑh are angles of location of OTH axis in space; min is the mass of internal frame with camera; lh is the distance of mass centre of internal frame (camera) from the centre of movement; Jxh1,Jyh1,Jzh1 are moments of inertia of external frame; Jxh,Jyh,Jzh are moments of inertia of internal frame (with camera); Mex,Min are moments of controlling forces influencing, respectively, external and internal frame; Mexg,Ming are moments of the force of gravity influencing respectively: external and internal frame; Mexg=0;Ming=minglhcos⁡⁡ϑh; and  M→dex,M→din are moments of friction forces in the bearings of, respectively, external and internal frame.We assume viscous friction:(30)Mdex=ηexψ˙h;Mdin=ηinϑ˙h,
where ηex is friction coefficient in suspension bearing of external frame and ηin is friction coefficient in suspension bearing of internal frame.Control momentsMex,Min of the head will be presented as follows [17–19]:
(31)Mex=Π(to,td)·Mexp(t)+Π(tt,te)·Mext(t),Min=Π(to,td)·Minp(t)+Π(tt,te)·Mint(t),
where Mexp,Minp are preprogrammed control moments and Mext,Mint are tracking control moments.Preprogrammed control momentsMexp,Minp, which set the head axis into the required motion, are determined from the following relationships:
(32)Mexp(t)=Π(to,td)·[kex(ψh-ψhr)+hex(ψ˙h-ψ˙hr)],Minp(t)=Π(to,td)·[kin(ϑh-ϑhr)+hin(ϑ˙h-ϑ˙hr)],
where kex,kin are gain coefficients of the OTH control system and hex,hin are attenuation coefficients of the OTH control system.Anglesϑhr,ψhr and their derivatives will be determined from the relationships (20).At the moment when the target will appear in the head coverage, that is,(33)|R→t-R→h|≤ρh,
head control passes to the tracking mode.Then, tracking control moments have the following form:(34)Mext(t)=Π(tt,te)·[kex(ψh-σ)+hex(ψ˙h-σ˙)],Mint(t)=Π(tt,te)·[kin(ϑh-ε)+hin(ϑ˙h-ε˙)].
Angles σ,ε will be determined from the relationships (3).Coefficientskex,kin,hex,hin are chosen in an optimum way due to the minimum deviation between the real and set path [15].It should be emphasized that the mathematical model of movement of the controlled observation and tracking head described with (29) allows for conducting a number of simulation tests of searching for and tracking a ground target from the UAV deck. Thanks to that, one can know about the areas of stability and permissible controls with the influence of kinematic excitations from the UAV deck.


## 4. Results of Computer Simulations

The presented algorithms of control of the movement of OTH performing the search and tracking of a ground target from the UAV deck have been tested on the example of a hypothetical UAV system. The following parameters were adopted:movement parameters of UAV(35)Hc=1500m,rc=500m,Vc=75m/s;movement parameters of the head(36)ts=10s,tl=20s,Rs=500m,ϕh=1deg⁡;movement parameters of the target(37)Vt=25m/s,χt=ωt·t,ωt=0.025rad/s;mass parameters of the head(38)min=3.375kg,Jxh1=0.22kgm2,Jyh1=0.114kgm2,Jzh1=0.117kgm2,Jxh=0.061kgm2,Jyh=0.035kgm2,Jzh=0.029kgm2;
the distance of mass centre of internal frame from the centre of movement
(39)lh=0.002m;
friction coefficients in suspension bearings of the head
(40)ηex=ηin=0.01Nms/rad.Kinematic excitations of the base (UAV) were adopted in the following form:(41)pc*=pc0*sin⁡(ν·t),qc*=qc0*cos⁡⁡(ν·t),rc*=rc0*sin⁡(ν·t),pc0*=qc0*=rc0*=0.5rad/s,ν=5rad/s.
For nonoptimum control, regulator coefficients amounted to
(42)kex=-5.0,hex=-1.5,kin=-5.0,hin=-1.5.
For optimum control, regulator coefficients amounted to
(43)kex=-20.0,hex=-5.0,kin=-20.0,hin=-5.0.Figure6 presents the results of computer simulation of movement kinematics of UAV as well as the head axis during searching the surface of the ground and tracking (laser lighting) a ground target.Figure 6
Path of movement of UAV, head axis, and the target during searching for and tracking the target.Figure7 presents the trajectory of movement of point H during scanning for and the movement of the target on the surface of the ground.Figure 7
Path of movement of pointH and the target on the surface of the ground.Figures8–10 present the desired and the real angles of deflection and inclination of the head axis, as well as control moments for the case when the head is influenced by kinematic excitations from UAV deck and the parameters of the regulator are not optimum.Figure 8
Time-dependent realϑh, ψh and desired ϑhr, ψhr angles specifying the location of the head axis for nonoptimum controls with the influence of disturbances.Figure 9
Real and desired trajectory of movement of the head axis for nonoptimum controls with the influence of disturbances.Figure 10
Time-dependent control momentsMin and Mex for nonoptimum parameters of the regulator with the influence of disturbances.Figures11, 12, and 13 present the desired and the real angles of deflection and inclination of the head axis, as well as control moments for the case when the head is not influenced by kinematic excitations from UAV deck and the parameters of the regulator are optimum.Figure 11
Time-dependent realϑh, ψh and desired ϑhr, ψhr angles specifying the location of the head axis for optimum controls without the influence of disturbances.Figure 12
Real and desired trajectory of movement of the head axis for optimum controls without the influence of disturbances.Figure 13
Time-dependent control momentsMin and Mex for optimum parameters of the regulator without the influence of disturbances.Figures14–16 present the desired and the real angles of deflection and inclination of the head axis, as well as control moments for the case when the head is influenced by kinematic excitations from UAV deck and the parameters of the regulator are optimum.Figure 14
Time-dependent realϑh,ψh and desired ϑhr,ψhr angles specifying the location of the head axis for optimum controls with the influence of disturbances.Figure 15
Real and desired trajectory of movement of the head axis for optimum controls with the influence of disturbances.Figure 16
Time-dependent control momentsMin and Mex for optimum parameters of the regulator without the influence of disturbances.Kinematic excitations from UAV deck adversely affect the operation of the head. It can particularly be seen in Figures11 and 14. In case of the nonoptimum choice of the parameters of the regulator, the deviations of the head axis from the set location are particularly visible (Figures 8 and 9). Smaller values of deviations can of course be achieved for optimum head controls (Figures 14 and 15). Control moments take small values.From the presented theoretical analysis and the simulation research of the process of scanning by OTH from UAV deck of the surface of the ground and then tracking the detected ground target, it can be inferred that(i)
it is possible to search for a target on the area of any size, which is only limited to the durability and range of UAV flight;(ii)
scanning is sufficiently precise;(iii)
the programme of scanning the surface of the ground is simple;(iv)
there occur relatively small values of OTH axis angle deviations from the nominal position;(v)
full autonomy of UAV during the mission of searching and laser lighting of the detected ground target secures the point of control against detection and destruction by an enemy;(vi)
the interference of an operator in controlling UAV may only be limited to cases of the vehicle’s total coming off from the set path or the loss of the target from OTH lens coverage (due to gusts of wind, explosions of missiles, etc.). Hence, the possibility of automatic sending of information about such occurrences to the control point and the possible taking of control over UAV flight by the operator should be introduced.


## 5. Conclusion

The considerations presented in this paper will allow us to conduct the research on the dynamics of OTH when manoeuvring UAV on which this device is mounted. It may enable the construction engineers to choose such parameters of OTH so that the transient processes occurring in the conditions of kinematic influence of UAV deck and at the moment of passing from scanning to tracking mode were minimized and disappeared in the shortest possible time.



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*Source: 934250-2014-09-08.xml*