Sampling-based path planning: a new tool for missile guidance
P. Pharpatara, B. Hérissé, R. Pepy, Y. Bestaoui 02-06/09/2013 - Würzburg, Germany
Introduction
Problem statement
Proposed solution : RRT+Dubins’ paths
Results
Conclusions & perspectives
Missile interception −→ Target detection by the radar station. I Mission preparation (À) : trajectories calculations. −→ Missile launch. I Midcourse guidance (Á) : I
I
ensure a proper collision course to the target with an acceptable velocity ; trajectory optimization with constraints.
−→ Target detection by the embedded radar. I Terminal guidance (Â) : I
engage the target at the Predicted Intercept Point (PIP).
PIP target Á À
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 radar beam
Ref.
Introduction
Problem statement
Proposed solution : RRT+Dubins’ paths
Results
Conclusions & perspectives
Objective To generate a missile-interceptor trajectory for the midcourse guidance (off-line or/and on-line) : I Optimal control problem : I
I
Terminal constraints at the PIP : I
I
I
maximize the final velocity (hit-to-kill). lower bound of terminal speed at the PIP (to ensure the target destruction) ; related orientation between the missile and the target at the PIP (due to the clearance of the embedded sensor).
Constraints related to the system/missile (here, single-stage missile) : I I I
structural limitation ; maximum angle of attack that can be balanced using the tail fins ; variation of air density.
=⇒ Complex, non-holonomic and non-linear problem 3/18
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Introduction
Problem statement
Proposed solution : RRT+Dubins’ paths
Results
Conclusions & perspectives
Closed-loop midcourse guidance laws I
Singular Perturbation Theory [4] ;
I
Linear Quadratic Regulators [6] ;
I
Fuzzy Logic [9] ;
I
Neural Network [13] ; Kappa guidance [8] :
I
I
I
take the final orientation into account ; maximize the final velocity (locally optimal).
-with control limitation -no control limitation
Trajectories given by Kappa guidance
Problem of analytical guidance laws (ex : kappa guidance) I
They cannot anticipate the future changes of flight conditions : I
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ex : loss of manoeuvrability at high altitude.
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Introduction
Problem statement
Proposed solution : RRT+Dubins’ paths
Results
Conclusions & perspectives
Trajectory generation using numerical methods [2]
I
State Dependant Riccati Equation (SDRE) technique [11] ;
I
Adaptive grid methods [1] ;
I
Pseudo-spectral method [12][10].
Problems of numerical methods I
Initialisation problem : I
I
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a good first guess is recommended to ensure the acquisition of a solution.
Trade-off between accuracy and efficiency in terms of computational effort.
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Introduction
Problem statement
Proposed solution : RRT+Dubins’ paths
Results
Conclusions & perspectives
Proposed solution
I
Combination of trajectory planning methods and optimal control methods, here : I
Rapidly-exploring Random Tree (RRT) [7] : I I
I
Dubins’ paths (Dubins’ metric) [5][3] : I
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it takes the future changes of flight conditions into account ; it can find a solution without any a priori guess. it is used to improve the optimality of the solution trajectory in 2D plane.
IFAC ACA 2013 - Würzburg, Germany
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Introduction
Problem statement
Proposed solution : RRT+Dubins’ paths
Results
Conclusions & perspectives
Ref.
Missile modelling in 2 Dimension ξ˙ = v,
(1)
mv˙ = fdrag (ρ, ||v||) + flift (ρ, ||v||) + fthrust − mg, θ˙ = q, I q˙ = τaero + τpert . flift fdrag
fthrust θ
α
Cg
v
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(3) (4)
I
I
fthrust lasts 20s after launch (single-stage missile) ; flift , fdrag depend on ρ and v : I
mg
(2)
I
ρ small : lost of manoeuvrability at high altitude ; v large : structural limitation.
Introduction
Problem statement
Proposed solution : RRT+Dubins’ paths
Results
Conclusions & perspectives
Mission and requirements (1) Mission I
xinit = [0 0 0 0]> with vertical launch for 1s ;
I
Xgoal = {x : kξ − ξ pip k < R, kvk > vmin , ∠(v, −vpip ) < φf } : Xgoal φf vpip φf
ξ pip vmin
R
I
vpip is in the horizontal direction ;
I
vmin = 500m/s ;
I
R = 500m ;
I
φf = π/8.
Exploration space
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I
X = {x : ξ ∈ [−20km, 20km] × [0km, 30km]} ;
I
Xfree = {x : alt(ξ) > 0, ||v(t > tboost )|| > vmin }.
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Introduction
Problem statement
Proposed solution : RRT+Dubins’ paths
Results
Conclusions & perspectives
Mission and requirements (2) Admissible control input U(t, x) = {avc : αc 6 αmax (t, x)} with
stb struct αmax (t, x) = min αmax (t, x), αmax (t, x)
where stb (t, x) : the maximum achievable angle of attack using tail fins ; αmax struct (t, x) : the structural limit which is given by the maximum αmax lateral acceleration abmax in body frame that the missile can suffer before it breaks.
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Introduction
Problem statement
Proposed solution : RRT+Dubins’ paths
Results
Conclusions & perspectives
Rapidly-exploring Random Trees - RRT [7]
What is RRT ? I
An incremental method designed to efficiently explore non-convex high-dimensional spaces.
Why choosing RRT ?
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I
It uses the complete model ;
I
It takes the future changes of environment into account ;
I
It can find a solution without any a priori guesses.
IFAC ACA 2013 - Würzburg, Germany
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Introduction
Problem statement
Proposed solution : RRT+Dubins’ paths
Results
Rapidly-exploring Random Tree - RRT [7] RRT Algorithm
G
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Conclusions & perspectives
Ref.
Introduction
Problem statement
Proposed solution : RRT+Dubins’ paths
Results
Conclusions & perspectives
Ref.
Rapidly-exploring Random Tree - RRT [7] RRT Algorithm
uniform distribution xrand
G
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Introduction
Problem statement
Proposed solution : RRT+Dubins’ paths
Results
Conclusions & perspectives
Ref.
Rapidly-exploring Random Tree - RRT [7] RRT Algorithm
xrand xnear (t)
Dubins’ metric
G
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Introduction
Problem statement
Proposed solution : RRT+Dubins’ paths
Results
Conclusions & perspectives
Ref.
Rapidly-exploring Random Tree - RRT [7] RRT Algorithm
xrand xnear (t) Proportional Navigation law [14]
G
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Introduction
Problem statement
Proposed solution : RRT+Dubins’ paths
Results
Conclusions & perspectives
Ref.
Rapidly-exploring Random Tree - RRT [7] RRT Algorithm
xrand xnew (t + ∆t) xnear (t)
Integration of complete model G with constraints, ∆t = 2s
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Introduction
Problem statement
Proposed solution : RRT+Dubins’ paths
Results
Conclusions & perspectives
Ref.
Rapidly-exploring Random Tree - RRT [7] RRT Algorithm
xrand xnew (t + ∆t) xnear (t)
Check if xnew ∈ Xfree
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G
Introduction
Problem statement
Proposed solution : RRT+Dubins’ paths
Results
Rapidly-exploring Random Tree - RRT [7] RRT Algorithm
G add xnew in G
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Conclusions & perspectives
Ref.
Introduction
Problem statement
Proposed solution : RRT+Dubins’ paths
Results
Conclusions & perspectives
NearestNeighbor What is Dubins’ metric (based on Dubins’ curve [5][3]) ? I
Analytical method used to define the shortest path between two states while considering their orientation ; xfinal xfinal
xinit
xfinal
(i) CCC type I
xinit
xinit
(ii) CSC types
Metric function : the length of the shortest Dubins’ path.
Why choosing Dubins’ metric ?
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I
Its optimality in 2D is assured ;
I
It considers the orientations of the two states.
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Ref.
Introduction
Problem statement
Proposed solution : RRT+Dubins’ paths
Results
Conclusions & perspectives
Ref.
Results : Comparisons and Discussions (1) 1) No saturation problem 4
x 10
350
3
||av c (αmax )|| ||av kappa || ||av RRT||
phase 1 (boost) phase 2
300
2.5 250
m/s2
altitude
2 1.5
200
150
1 100
0.5 50
0 0
−2
−1.5
−1
−0.5 0 0.5 horizontal distance
1
1.5
2
0
0.1
4
x 10
0.2
0.3
0.4
0.5
0.6
0.7
0.8
0.9
t/tf
Lateral accelerations along the solution Generated trajectories trajectories √ √ f I < π/8 and ∠(vkappa , −vpip ) < π/8 ; √ √ I ||vf || = 1807m/s > 500m/s and ||vf ; RRT kappa || = 1717m/s > 500m/s f ∠(vRRT , −vpip )
I RRT and kappa : respect the limit of control inputs. 13/18
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1
Introduction
Problem statement
Proposed solution : RRT+Dubins’ paths
Results
Conclusions & perspectives
Ref.
Results : Comparisons and Discussions (2) 2) With saturation problem 4
x 10
500
3
||av c (αmax )|| ||av kappa || ||av RRT||
450
2.5
400
350
2
m/s2
altitude
300
1.5
250
200
1 150
phase 1 (boost)
0.5
100
phase 2
50
0 0
−2
−1.5
−1
−0.5 0 0.5 horizontal distance
1
1.5
2 4
x 10
0
0.1
0.2
0.3
0.4
0.5
0.6
0.7
0.8
0.9
t/tf
Lateral accelerations along the solution Generated trajectories trajectories √ I ∠(vf , −vpip ) < π/8 and ∠(vf kappa , −vpip ) = 0.62 > π/8X ; RRT √ I ||vf || = 1552m/s > 500m/s ; RRT I RRT anticipates the loss of manoeuvrability at the end of the trajectory but kappa doesn’t. 14/18
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Introduction
Problem statement
Proposed solution : RRT+Dubins’ paths
Results
Conclusions & perspectives
Conclusions
Advantages I I
Satisfaction of constraints by integrating the complete model ; It anticipates future flight conditions : I
I
for example : for the 2nd scenario, a back-turn can be found.
A solution can be found without any a priori guess.
Drawbacks
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I
Obtained solutions are not optimal ;
I
Number of iterations to find a solution can be large depending on how difficult the scenario is (ok for off-line trajectory generation).
IFAC ACA 2013 - Würzburg, Germany
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Introduction
Problem statement
Proposed solution : RRT+Dubins’ paths
Results
Conclusions & perspectives
Perspectives
I
Evolution of distance between RRT solution and the optimal one : I I
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maximize the final velocity ; minimize the flight time.
I
Improve the computing time by reducing X ;
I
Improve the metric and the selection of control input ;
I
2D→3D.
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Introduction
Problem statement
Proposed solution : RRT+Dubins’ paths
Results
Conclusions & perspectives
References I [1]
D. A. Anisi, Adaptive node distribution for on-line trajectory planning, Congress of the International Council of the Aeronautical Sciences (ICAS) (2006).
[2]
J. T. Betts, Survey of munmerical methods for trajectory optimization, Journal of Guidance, Control, and Dynamics 21 (1998), no. 2, 193–207.
[3]
J. D. Boissonnat, A. Cérézo, and J. Leblond, Shortest paths of bounded curvature in the plane, Tech. report, Institut National de Recherche en Informatique et en Automatique, 1991.
[4]
V. H. L. Cheng and N. K. Gupta, Advanced midcourse guidance for air-to-air missiles, Journal of Guidance, Control, and Dynamics 9 (1986), no. 2, 135–142.
[5]
L. E. Dubins, On curves of minimal length with a constraint on average curvature and with presribed initial and terminal position and tangents, American Journal of Mathematics 79 (1957), 497–516.
[6]
F. Imado, T. Kuroda, and S. Miwa, Optimal midcourse guidance for medium-range air-to-air missiles, Journal of Guidance, Control, and Dynamics 13 (1990), no. 4, 603–608.
[7]
S. M. LaValle, Planning algorithms, Cambridge University Press, 2006.
[8]
C. F. Lin, Modern navigation guidance and control processing, Prentice-Hall, Inc., 1991.
[9]
C. L. Lin and Y. Y. Chen, Design of fuzzy logic guidance law against high-speed target, Journal of Guidance, Control, and Dynamics 23 (2000), no. 1, 17–25.
[10] J. A. Lukacs and O. A. Yakimenko, Trajectory-shape-varying missile guidance for interception of ballistic missiles during the boost phase, AIAA (2007). [11] P. K. Menon, T. Lam, L. S. Crawford, and V. H. Cheng, Real-time computational methods for sdre nonlinear control of missiles, American Control Conference (2002), 232–237. [12] J.-W. Park, M.-J. Tahk, and H.-G. Sung, Trajectory optimization for a supersonic air-breathing missile system using pseudo-spectral method, International Journal of Aeronautical and Space Sciences 10 (2009), 112–121. 17/18
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Introduction
Problem statement
Proposed solution : RRT+Dubins’ paths
Results
Conclusions & perspectives
References II
[13] E. J. Song and M. J. Tahk, Real-time neural-network midcourse guidance, Control Engineering Practice 9 (2001), no. 10, 1145 – 1154. [14] P. Zarchan, Tactical and strategic missile guidance, second ed., Progress in Astronautics and Aeronautics, vol. 157, America Institute of Aeronautics and Astronautics, Inc. (AIAA), 1994.
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