The rotorcraft flight simulation is a multidisciplinary mathematical model that may be used to simulate a wide variety of helicopter or V/STOL aircraft configurations using a digital computer. Aircraft performance, stability and control, and maneuver characteristics, as well as rotor blade loads, may be estimated using this analysis. The fuselage, main rotor, tail rotor, wing, elevator, fin/rudder, jet thrust, and weapon recoil are treated as separate aircraft components, allowing detailed representation of the aircraft for design or detailed analysis applications. Six rigid-body fuselage degrees of freedom and up to six rotor blade elastic degrees of freedom for each of two rotors are accounted for. Input for the simulation is divided into logical blocks in an easy-to-understand format. The rotor blade elastic degrees of freedom are omitted if stiffness and mass properties are not known. Output includes aircraft trim attitude, control positions, performance rotor loads, stability and control characteristics, and detailed maneuver response. (Modified author abstract)
General Description of the Rotorcraft Flight Simulation Computer Program (G-81)
1973
58 pages
Report
No indication
English
Parallel rotorcraft flight simulation
AIAA | 1993
|Computer flight testing of rotorcraft
Engineering Index Backfile | 1965
|Computer Flight Testing of Rotorcraft
British Library Conference Proceedings | 2006
|In-Flight Rotorcraft Acoustics Program
NTRS | 1996
|In-Flight Rotorcraft Acoustics Program
NTIS | 1996
|