Publication Date:
2019-07-13
Description:
The paper discusses the design of a higher harmonic blade pitch control system for flight testing on an OH-6A helicopter. Alternative designs for both the mechanical and electronic subsystems are also presented. Among the recommendations set forth are: (1) use electronic analog methods instead of FFT software, delegating spectral analysis and self testing to an Electronic Control Unit; (2) use a digital rather than analog computer for increased flexibility in solution processing; and (3) locate HHC actuators in the nonrotating system and separate these actuators from the primary control system. It is concluded that a target weight for a prototype control system would be less than 1% of design gross weight and the production weight of the future HHC system may be 0.5 of the weight of the aircraft.
Keywords:
AIRCRAFT STABILITY AND CONTROL
Type:
AHS PAPER 80-67
,
AIAA PAPER 80-0668
,
Structures, Structural Dynamics, and Materials Conference; May 12, 1980 - May 14, 1980; Seattle, WA
Format:
text
Permalink
