Trajectory optimization based on differential inclusion (Revised)

Seywald, Hans

doi:10.2514/3.21224

Cited by 143 publications

(57 citation statements)

References 2 publications

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“…Singular controls affect the convergence of the collocation method, but do not considerably influence the performance of the differential inclusion scheme. This is consistent with previous results (see Seywald (1994)). In addition, the differential inclusion scheme describes the system with smaller number of decision variables and constraints than collocation.…”

Section: Discussionsupporting

confidence: 83%

“…Betts and Huffman (1993) discuss trapetzoidal, HermiteSimpson and Runge-Kutta discretization. In the following we describe two schemes, direct collocation and a recently proposed method based on differential inclusions Seywald (1994). In the former approach the states and controls are approximated by piecewisely defined low-order polynomials.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Aircraft trajectory optimization using nonlinear programming

Raivio¹,

Ehtamo²,

Hämäläinen³

1996

System Modelling and Optimization

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Section: Discussionsupporting

confidence: 83%

Section: Introductionmentioning

confidence: 99%

Aircraft trajectory optimization using nonlinear programming

Raivio¹,

Ehtamo²,

Hämäläinen³

1996

System Modelling and Optimization

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“…Seywald et al introduced an approach based on the representation of the dynamical system in terms of differential inclusions. This method employs the concepts of hodograph space and attainable sets (see [12,13] [20,21].…”

Section: Methodsmentioning

confidence: 99%

Trajectory Shaping of Surface-to-Surface Missile With Terminal Impact Angle Constraint

Subchan¹

2010

MST

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This paper presents trajectory shaping of a surface-to-surface missile attacking a fixed with terminal impact angle constraint. The missile must hit the target from above, subject to the missile dynamics and path constraints. The problem is reinterpreted using optimal control theory resulting in the formulation of minimum integrated altitude. The formulation entails nonlinear, two-dimensional missile flight dynamics, boundary conditions and path constraints. The generic shape of optimal trajectory is: level flight, climbing, diving; this combination of the three flight phases is called the bunt manoeuvre. The numerical solution of optimal control problem is solved by a direct collocation method. The computational results is used to reveal the structure of optimal solution which is composed of several arcs, each of which can be identified by the corresponding manoeuvre executed and constraints active.

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“…, x(t N ), u(t N )), and M = dim y = (n + 1)N . Seywald [28] suggested an improvement to the previous method (see also [2] page 362). Following this work, one first solves a subset of system dynamics in (14) for the the control in terms of combinations of the state and its time derivative.…”

Section: Numerical Solution Using Collocationmentioning

confidence: 99%

Online Control Customization via Optimization‐Based Control

Samad

Balas

2003

Software‐Enabled Control

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In this chapter, we present a framework for online control customization that makes use of finite-horizon, optimal control combined with real-time trajectory generation and optimization. The results are based on a novel formulation of receding-horizon optimal control that replaces the traditional terminal constraints with a control Lyapunov function-based terminal cost. This formulation leads to reduced computational requirements and allows proof of stability under a variety of realistic assumptions on computation. By combining these theoretical advances with advances in computational power for real-time, embedded systems, we demonstrate the efficacy of online control customization via optimization-based control. The results are demonstrated using a nonlinear, flight control experiment at Caltech.

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Trajectory optimization based on differential inclusion (Revised)

Cited by 143 publications

References 2 publications

Aircraft trajectory optimization using nonlinear programming

Aircraft trajectory optimization using nonlinear programming

Trajectory Shaping of Surface-to-Surface Missile With Terminal Impact Angle Constraint

Online Control Customization via Optimization‐Based Control

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