OTIS past, present and future

Hargraves, C. R.; Paris, Stephen; Vlases, W.

doi:10.2514/6.1992-4530

Cited by 11 publications

(4 citation statements)

References 12 publications

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“…Because of this, direct methods, implemented in industry standard tools such as POST and OTIS, are more commonly used. [15][16][17] The direct method for solving optimal control problems approximates the control function as a finite set of parameters. Equation 3 is the mathematical formulation of this process.…”

Section: A Direct Methods Trajectory Optimizationmentioning

confidence: 99%

Capturing the Global Feasible Design Space for Launch Vehicle Ascent Trajectories

Steffens

Mavris

Edwards

2015

AIAA Atmospheric Flight Mechanics Conference

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A common approach to solving infinite dimensional optimal control problems, such as in launch vehicle trajectory optimization, is to approximate the optimal control function as a set of parameters. This process, known as the direct method, transcribes the optimal control problem into a finite dimensional parameter optimization problem. Traditionally, subject matter experts and trajectory analysts work manually to find usable trajectories by changing the initial guess for the control parameters. This paper presents a method to capture the feasible design space of a launch vehicle trajectory problem. The result is a region of feasible values for the launch vehicle control parameters. In this context, feasibility is defined by the trajectory reaching the termination criteria, thereby returning a function evaluation. The method is applied to a Delta IV Medium launch vehicle. This vehicle is used because it represents the challenges of trajectory optimization for ETO launch vehicles while not being overly complex. Two ways of sampling the control parameter design space to determine feasibility are compared. Results are represented using design variable limits and the global feasible space is shown directly using scatter-plot matrices.

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Section: A Direct Methods Trajectory Optimizationmentioning

confidence: 99%

Capturing the Global Feasible Design Space for Launch Vehicle Ascent Trajectories

Steffens

Mavris

Edwards

2015

AIAA Atmospheric Flight Mechanics Conference

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“…8). A user can simulate and optimize a wide variety of vehicles such as aircraft, missiles, reentry vehicles, ascent vehicles, satellites, and interplanetary vehicles.…”

Section: Otismentioning

confidence: 99%

Mars ascent vehicle gross lift-off mass sensitivities for robotic Mars sample return

Dux

Huwaldt

Mckamey

et al. 2011

2011 Aerospace Conference

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“…DCNLP converts a TPBVP into a nonlinear programming problem [4]. It divides the trajectory into segments and approximates the solution of EOM by cubic polynomials within each segment.…”

Section: Introductionmentioning

confidence: 99%

Solving a Five-linked Robotic Manipulator CNC Problem Using Direct Collocation with Nonlinear Programming

Mei¹,

Pan²,

Chen³

et al. 2013

Proceedings of the 2nd International Conference on Computer Science and Electronics Engineering (ICCSEE 2013)

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Abstract-Computer numerical control (CNC) and robotic welding have long been applied to industrial manufacturing in production lines. This paper introduces optimal control to layout the maneuvering sequence for a five-linked manipulator arm. Two-point boundary-value problem (TPBVP) is inevitable in most of the dynamic optimal control problem. Direct collocation with Nonlinear Programming (DCNLP) converts a TPBVP into a nonlinear programming problem. DCNLP has been extensively applied in solving the space and aircraft control problems but is not much adopted in solving robotic optimization problems. The paper requires a manipulator to weld up two cylinders which are intersecting and perpendicular to each other. A least energy maneuvering sequence is expected.

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OTIS past, present and future

Cited by 11 publications

References 12 publications

Capturing the Global Feasible Design Space for Launch Vehicle Ascent Trajectories

Capturing the Global Feasible Design Space for Launch Vehicle Ascent Trajectories

Mars ascent vehicle gross lift-off mass sensitivities for robotic Mars sample return

Solving a Five-linked Robotic Manipulator CNC Problem Using Direct Collocation with Nonlinear Programming

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