A cyclocopter propelled by the cycloidal blade system, which can be described as a horizontal rotary wing, is a new concept of VTOL vehicle. In this paper, structural design and analysis are carried out for the aerodynamically optimized cyclocopter rotor system. Design variables such as stacking sequence (ply angles), number of plies and locations of spars of composite blade are determined through MSC/NASTRAN, RSM and some other optimizing processes. The maximum stress obtained by static analysis of each parts of the rotor is within the failure criteria. The rotor system is designed for the purpose of avoiding possible dynamic instabilities by inconsistency between frequencies of rotor rotation and some low natural frequencies of rotor. Also dynamic analysis for the airframe which supports the rotor, engine, etc. is carried out.
[1]
Mitsuo Gen,et al.
Genetic algorithms and engineering optimization
,
1999
.
[2]
Yun,et al.
A New VTOL UAV Cyclocopter with Cycloidal Blades System
,
2004
.
[3]
John B Wheatley.
Simplified aerodynamic analysis of the cyclogiro rotating wing system
,
1933
.
[4]
James H. Boschma,et al.
Construction and testing of a new aircraft cycloidal propeller
,
1999
.
[5]
Frederick Kurt Kirsten.
Cycloidal propulsion in air
,
1935
.
[6]
Douglas C. Montgomery,et al.
Response Surface Methodology: Process and Product Optimization Using Designed Experiments
,
1995
.