A study of advanced guidance laws for maneuvering target interception Student: Felix Vilensky...
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![Page 1: A study of advanced guidance laws for maneuvering target interception Student: Felix Vilensky Supervisor: Mark Moulin Control & Robotics Laboratory.](https://reader031.fdocuments.net/reader031/viewer/2022032523/56649d815503460f94a65742/html5/thumbnails/1.jpg)
A study of advanced guidance laws for A study of advanced guidance laws for maneuvering target interceptionmaneuvering target interception
Student: Felix Vilensky Student: Felix Vilensky
Supervisor: Mark MoulinSupervisor: Mark Moulin
Control & Robotics LaboratoryControl & Robotics Laboratory
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Introduction
This project deals with missile-target interception. This is a highly non-linear and non stable control problem.
We work with a simplified 2D model. We will discuss the following guidance laws:
PN (Proportional Navigation). Saturated PN. TDLQR(Time dependant LQR). OGL (Optimal guidance law).
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Plant - Interception problem
2T Ta ca
.. . .
2.. .
2 sin( ) cos( )
cos( ) sin( )
T M
T M
r r a a
r r a a
0.0008c
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PN controller
PlantPlant
PN ControllerPN Controller
rTarget Target
AccelerationAcceleration ModelModel
. .
Ma N r 3.85N
Ta
Ma
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PN controller - references
Dhar,A.,and Ghose,D.(1993)Capture region for a realistic TPN guidance law.
Chakravarthy,A.,and Ghose,D.(1996)Capturability of realistic Generalized True Proportional Navigation.
Moulin,M.,Kreindler,E.,and ,Guelman,M(1996).Ballistic missile interception with bearings-only measurements.
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PN controller-Command acceleration and relative distance vs. time
0 5 10 15 20 25 30 35 40 45 5030
40
50
60
70
80
90
100
110
120
130aM vs time
t[sec]
aM[m
/s^2
}
3.85, 0.1745 , 0.261 , 0.0051sec
1787 , 80000 , 0.96seci
i
r i i
radN rad rad
mV r m rad
0 5 10 15 20 25 30 35 40 45 500
1
2
3
4
5
6
7
8x 10
4
t[sec]
r[m
]
distance vs time
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PN controller – Capturability limits
Initial parameters Capturability limits
<86977
<-1683
<= -0.82
>=0.04
>=0.174
(-0.0068,0.0232)
rV
r
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PN controller -conclusions
The performance of the PN controller is quite good. It enables intercepting a target in a wide range of initial conditions.
Yet, the command acceleration is growing with time. And a real physical system cannot maintain an acceleration that is growing towards non physical values.
We seek to find a controller that will work under the constraint of limited (saturated) command
acceleration.
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Saturated PN
The first and naive approach is to retain the PN controller and just to add at its output a lowpass filter and a saturation to get the command acceleration.
LP filterLP filter
We use a Butterworth LPF of order 30 with cutoff frequency of 8 rad/sec. This filter will ensure that the command acceleration won’t change too rapidly for the missile to follow.
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Saturated PN controller - Command acceleration and relative distance vs. time
3.85, 0.1745 , 0.261 , 0.0051sec
2300 , 80000 , 0.96seci
i
r i i
radN rad rad
mV r m rad
0 5 10 15 20 25 30 35 400
10
20
30
40
50
60
t[sec]
aM[m
/s2 ]
aM vs time
0 5 10 15 20 25 30 35 400
1
2
3
4
5
6
7
8x 10
4
t[sec]
r[m
]
distance vs time
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Linear controllers
Linear or partially linear controllers are easier to design than nonlinear ones.
Linear control can be more easily optimized than nonlinear one.
Recent papers used linear control design methods:
Hexner,G.,and Shima,T.(2007)Stochastic optimal control guidance law with bounded acceleration.
Hexner,G.,Shima,T.,and Weiss,H.(2008)LQG guidance law with bounded acceleration
command.
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Calculate every fixed interval of time (T) a new infinite horizon LQR.
Use the following state variables:
Each time linearize the plant around:
i.e., around the relative speed and the distance at the time of calculation.
Using this LQR controller till the next calculation. LQR recalculation period:100ms.
Plant sampling period: about 50 ms.
Time dependant LQR
, ,r r
0 00, , 0r r r V
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Time dependant LQR
This linear system we use in each calculation:
0
00
0 1 0 0
0 0 0 sin( ) ( )
2 cos( )0 0
M
r r
r r a
V
rr
The following J parameter is being minimized:2
0( ( ) )
0.001 0 0
0 0.01 0 , 1
0 0 1000000
TMJ x Qx a dt
Q
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Time dependant LQR
LQR calculatorLQR calculator
PlantPlant
Target Target AccelerationAcceleration
ModuleModule
Ta
Ma
LQR controllerLQR controllerLPF andLPF and saturationsaturation
clockclock
State vector
Gain vector
controller
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Time dependant LQR – Command acceleration behavior
0 5 10 15 20 25 30 35 400
10
20
30
40
50
60The command acceleration vs. time for saturated Time dependant LQR
t[sec]
aM[m
/s2 ]
8 8.5 9 9.5 10 10.5 11 11.5 12 12.5
18
20
22
24
26
28
30
32
34
36
38
t[sec]
aM[m
/s2 ]
A sketch of command acceleration vs. time for not saturated Time dependant LQR
3.85, 0.1745 , 0.261 , 0.0051sec
2300 , 80000 , 0.96seci
i
r i i
radN rad rad
mV r m rad
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Pure LQR vs. TDLQR
The TDLQR is designed using methods and intuition of optimal linear control.
TDLQR is linear only in each time slice between calculations.
There is a well known LQR guidance law, which is linear through all the engagement time. It is called OGL – Optimal Guidance Law.
While TDLQR is based on infinite horizon LQR, the OGL is a finite horizon LQR, which means that its control gain varies with time.
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Optimal Guidance Law
The OGL is obtained using the following linearization of the plant:
Where:sin( )
is the target acceleration.
is the actual applied missile acceleration( ).
is the commanded acceleration(the output of the controller).
is the end of engagement time.
is the time
T
L M
c
F
y r
n
n a
n
t
T
constant of the guidance system.
Thangavelu,R.,and Pardeep,S.(2007)A differential evolution tuned Optimal Guidance Law.
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Optimal Guidance Law
The OGL minimizes:
The optimal control is given by:
2
0, ( ) 0
Ft
c FJ n dt y t
The OGL output is then passed through LPF an saturation, as explained earlier to get the command acceleration.
2 22
2
3 2 2
[ 0.5 ( 1 )]
where
6 ( 1 )and
2 3 6 6 12 31
1
xc go T go L
go
go F
x
x x
L
c
Nn y yt n t n T e x
t
t t tx
T T
x e xN
x x x xe en
n sT
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Performance Analysis
Miss distance Vs. intial relative speed in PN
0
10000
20000
30000
40000
50000
60000
-3500 -3000 -2500 -2000 -1500 -1000 -500 0
Vr[m/s]
Mis
s di
stan
ce[m
]
Miss distance vs. initial relative speed in saturated PN(-60,60)
0
10000
20000
30000
40000
50000
60000
-4500 -4000 -3500 -3000 -2500 -2000 -1500 -1000 -500 0
Vr[m/s]
Mis
s di
stan
ce[m
]
Miss distance vs. initial relative speed for PN (left) and saturated PN (right) controllers.
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Performance Analysis
Miss distance vs. initial relative velocity for Time Dependant LQR, saturated PN and OGL controllers.
Miss distance vs. initial relative velocity in saturated PN,TDLQR and OGL(-60,60)
0
10000
20000
30000
40000
50000
60000
70000
-4500 -4000 -3500 -3000 -2500 -2000 -1500 -1000 -500 0
Vr[m/s]
Mis
s d
ista
nce
[m]
SatPN
TDLQR
OGL
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Performance Analysis
Miss distance vs. maximal command acceleration for TDLQR and saturated PN
0
200
400
600
800
1000
1200
1400
1600
1800
2000
0 20 40 60 80 100 120 140 160 180
Maximal command acceleration[m/s^2]
Mis
s di
stan
ce[m
]
TDLQR
SatPN
Miss distance vs. maximal command acceleration for Time Dependant LQR and saturated PN (left) and for OGL (right).
Miss distance vs maximal command acceleration for OGL
18400
18450
18500
18550
18600
18650
18700
18750
18800
18850
0 20 40 60 80 100 120 140 160 180
Maximal command acceleration[m/s^2]
Mis
s di
stan
ce[m
]
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Performance Analysis
Miss distance vs. initial distance for Time Dependant LQR, saturated PN and OGL controllers.
Miss distance vs. initial distance for OGL,TDLQR and saturated PN(-60,60)
0
10000
20000
30000
40000
50000
60000
70000
80000
90000
0 20000 40000 60000 80000 100000 120000 140000
Initial distance[m]
Mis
s d
ista
nce
[m]
OGL
SatPN
TDLQR
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Performance Analysis
Miss distances vs. initial distances for Time Dependant LQR, saturated PN and OGL controllers (for relatively small initial distances).
Initial distance
Saturated PN (miss distance)
Time dependant LQR (miss distance)
OGL(miss distance)
10000 304.6893 301.162 250.6541
20000 231.6058 130.8969 18.3121
40000 26.603 182.5942 1811.2
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Performance Analysis-Results
The effect of the lowpass filter and saturation block provides an optimal initial relative velocity for interception.
The capturability is improved when the maximal command acceleration is increased for TDLQR and saturated PN, and gets worse for OGL.
For large initial distances the miss distance grows monotonically with the initial distance.
For small initial distances an optimal initial distance results in a minimal miss distance.
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Performance Analysis-Conclusions
TDLQR has a clear advantage in the performance evaluation over both saturated PN and OGL .
The miss distance for OGL is growing with the maximal command acceleration. OGL doesn’t update linearization and thus applies non optimal command acceleration.
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Performance Analysis-Conclusions
The optimum of initial relative velocity is obtained, since for high velocities the command acceleration cannot be high enough to complete the maneuver needed to get the missile into collision course with the target.
The optimum of initial distance is obtained, since for small enough initial distances the missile covers too much distance (outruns the target) before the maneuver needed to get it into collision course with the target is completed.