A Mathematical Model of a Single Main Rotor Helicopter for ... - Read
A Mathematical Model of a Single Main Rotor Helicopter for ... - Read
A Mathematical Model of a Single Main Rotor Helicopter for ... - Read
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1. Report No.<br />
NASA TM-84281<br />
4. Title and Subtitle<br />
A MATHEMATICAL MODEL OF A SINGLE MAIN ROTOR<br />
HELICOPTER FOR PILOTED SIMULATION<br />
7. Author(s1<br />
Peter D. Talbot, Bruce E. Tinling,<br />
William A. Decker, and Robert T. N. Chen<br />
9. Per<strong>for</strong>ming Organization Name and Address<br />
NASA Ames Research Center<br />
M<strong>of</strong>fett Field, Cali<strong>for</strong>nia 94035<br />
12. Sponsoring Agency Name and Address<br />
National Aeronautics and Space Administration<br />
Washington, D.C. 20546<br />
15. Supplementary Notes<br />
7. Key Words 6uggestd by Authorlsl) <strong>Helicopter</strong><br />
Flight simulation; Handling qualities<br />
<strong>Helicopter</strong> aerodynamics<br />
<strong>Helicopter</strong> flight dynamics<br />
<strong>Helicopter</strong> stability and control aug-<br />
mentation sy s tem<br />
2. Govmmrnt Acclrion No. 3. Rucipient's Catalog No.<br />
I<br />
.<br />
5. Report Date<br />
SeDtember 1982<br />
6. Per<strong>for</strong>ming Orgniration codr<br />
8. Per<strong>for</strong>ming Organization Report No.<br />
A-9033<br />
10. Work Unit No.<br />
T-6292Y<br />
11. Contract or Grant No.<br />
13. Type <strong>of</strong> Report and Pari4 Cotmod<br />
Technical Memorandum<br />
14. Sponrorir) Agency Code<br />
Point <strong>of</strong> Contact: William A. Decker, Mail Stop 211-2, NASA Ames Research<br />
Center, M<strong>of</strong>fett Field, CA 94035 (415) 965-5362 or FTS 448-5362<br />
18. Distribution Statement<br />
Unlimited<br />
~~ ~~<br />
16. Abstract<br />
This report documents a helicopter mathematical model suitable <strong>for</strong><br />
piloted simulation <strong>of</strong> flying qualities. The mathematical model is a non-<br />
linear, total <strong>for</strong>ce and moment model <strong>of</strong> a single main rotor helicopter. The<br />
model has ten degrees <strong>of</strong> freedom: six rigid-body, three rotor-flapping, and<br />
the rotor rotational degrees <strong>of</strong> freedom. The rotor model assumes rigid<br />
blades with rotor <strong>for</strong>ces and moments radially integrated and summed about<br />
the azimuth. The fuselage aerodynamic model uses a detailed representation<br />
over a nominal angle <strong>of</strong> attack and sideslip range <strong>of</strong> +15", and it uses a<br />
simplified curve fit at large angles <strong>of</strong> attack or sideslip. Stabilizing<br />
surface aerodynamics are modeled with a lift curve slope between stall<br />
limits and a general curve fit <strong>for</strong> large angles <strong>of</strong> attack. A generalized<br />
stability and control augmentation system is described. Additional computer<br />
subroutines provide options <strong>for</strong> a simplified engine/governor model, atmo-<br />
pheric turbulence, and a linearized six-degree-<strong>of</strong>-freedom dynamic model <strong>for</strong><br />
stability and control analysis.<br />
Subject Category - 08<br />
Unclassified Unclassified<br />
I 55 I A04<br />
*For =le by the National Technical In<strong>for</strong>mation Stvice. Springfield, Virginia 22161
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