From APMonitor Documentation

Apps: Rocket Launch: Classic Optimal Control

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.

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

Download Rocket Launch Planning Solution in MATLAB and Python

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Page last modified on August 26, 2016, at 05:14 PM