Analytical Determination of a Helicopter Height Velocity Diagram

Abstract

A helicopter height velocity (HV) diagram was analytically constructed using optimal control techniques. A three degree of freedom, point-mass, dynamic model was developed and validated with ight test data. An induced velocity calculation was incorporated which addressed the axB;effects of vortex ring state. The problem was posed as an open final time, constrained initial state, constrained xC;final state problem, with the objective function as a weighted sum of the initial altitude and quadratic controls. This formulation was solved using direct pseudo-spectral collocation and adaptive mesh refinement as implemented by the GPOPS-II software suite. Proper adjustment of path constraints was crucial in achieving solutions which were comparable with ight test data. Results compare favorably with flight test data and previous analytical HV diagrams.

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Document Details

Document Type
Technical Report
Publication Date
Mar 22, 2018
Accession Number
AD1056577

Entities

People

  • Michael J. Harris

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Aerial Warfare
  • Air Force
  • Aircraft Equipment
  • Aircrafts
  • Airframes
  • Algorithms
  • Altitude
  • Calculus Of Variations
  • Case Studies
  • Computational Science
  • Computer Programming
  • Control Systems
  • Engineering
  • Equations
  • Equations Of Motion
  • Fixed Wing Aircraft
  • Ground Effect
  • Helicopters
  • Level Flight
  • Optimization
  • Particle Swarm Optimization
  • Rotary Wing Aircraft
  • Tilt Rotor Aircraft
  • United States

Readers

  • Computational Fluid Dynamics (CFD)
  • Computational Modeling and Simulation
  • Control Systems Engineering.