Rocket Launch: Classic Optimal Control

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August 26, 2016, at 05:14 PM by -
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!!!! Problem Statement

 minimize tf

 subject to
  ds/dt = v
  dv/dt = (u-0.2*v^2)/m
  dm/dt = -0.01 * u^2

 path constraints
  0.0 <= v(t) <= 1.7
  -1.1 <= u(t) <= 1.1
 initial boundary conditions
  s(0) = 0
  v(0) = 0
  m(0) = 1

 final boundary conditions
  s(tf) = 10.0
  v(tf) = 0.0

!!!! Solution
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Attach:download.png [[|Download Rocket Launch Planning Solution in MATLAB and Python]]
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(:title Rocket Launch: Classic Optimal Control Problem:)
(:title Rocket Launch: Classic Optimal Control:)
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A rocket burn trajectory is desired to minimize a travel time between a starting point and a final point, 10 units of distance away. The thrust can be between an upper limit of 1.1 and a lower limit of -1.1. The initial and final velocity must be zero and the maximum velocity can never exceed 1.7. It is also desirable to minimize the use of fuel to perform the maneuver. There is a drag resistance the is proportional to the square of the velocity and mass is lost as the fuel is burned during thrust operations.

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(:title Rocket Optimization:)
(:title Rocket Launch: Classic Optimal Control Problem:)
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<iframe width="560" height="315" src="" frameborder="0" allowfullscreen></iframe>
August 22, 2016, at 11:17 PM by -
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(:title Rocket Optimization:)
(:keywords Python, MATLAB, nonlinear control, Rocket, Goddard, model predictive control, dynamic programming:)
(:description Minimize final time for rocket launch by manipulating the force exerted by the thruster. This is a classic dynamic optimization problem benchmark used in many research papers to test the application of new algorithms.:)