Finding a State-Space Representation for Helicopter Pitch Angle Control

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SUMMARY

The discussion focuses on deriving a state-space representation for controlling the pitch angle (theta) of a helicopter by regulating the rotor angle (u). The user seeks clarification on the formulation of the A matrix, specifically the equation X3' = 9.8*theta - 14.3*theta' - 0.198*theta, which has been identified as incorrect. The objective is to achieve accurate local linearization to effectively control the helicopter's pitch angle.

PREREQUISITES
  • Understanding of state-space representation in control systems
  • Familiarity with linearization techniques in control theory
  • Knowledge of helicopter dynamics and pitch control mechanisms
  • Proficiency in mathematical modeling and matrix algebra
NEXT STEPS
  • Research state-space representation techniques for dynamic systems
  • Learn about local linearization methods in control theory
  • Study helicopter dynamics focusing on pitch control strategies
  • Explore the derivation and application of A matrices in control systems
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Control engineers, aerospace engineers, and students studying dynamic systems and control theory, particularly those interested in helicopter dynamics and pitch angle regulation.

Nico Frontmann
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I need help finding a state-space representation for the given system and locally linearizing it...

15w1ls.jpg

Objective is to control the pitch angle theta, as an output, of the helicopter by regulating the rotor angle u, as an input.

This is what I've done, but apparently it isn't correct, and I don't understand why:
k9uixy.jpg
 
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in your A matrix you are saying X3'=9.8*theta-14.3*theta'-0.198*theta.
 

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