Conceptual Design of a Low-Cost Training Helicopter
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Conceptual Design of a Low-Cost Training Helicopter Objective of Thesis • To design a concept helicopter that is low in cost and suitable for training Research Approach • Use a set of performance requirements to conduct parametric analysis and determine possible design configurations Results • A concept helicopter was developed, and its performance and cost are deemed to be comparable to existing market favourites Benefits • Incentivise labour market to increase pool of private-license pilots • Reduce operating cost of companies that conduct in-house pilot training Future Work • Update weight estimation equations used in the parametric analysis • Assess performance and cost of British Experimental Rotor Program (BERP) rotor blade • Assess performance and cost of diesel piston engines Author: Liu Jianlin Thesis advisor: Jack A. Stockford Components Parameter Specifications Main rotor Radius 4.4 m Tip speed 213 m/s Solidity 0.036 Chord 0.25 m Number of rotor blades 2 Airfoil NACA 0015 Direction of rotation Anti-clockwise (view from above) Tail rotor Radius 0.792 m Tip speed 213 m/s Solidity 0.0996 Chord 0.124 m Number of rotor blades 2 Airfoil NACA 0015 Direction of rotation Bottom blade advancing Engine Type Reciprocating (Lycoming O-360) Power at sea level 134.2 kW Fuselage Length 6.36 m Width 1.2 m Landing gear Type Fixed skids 8.8 1.6 0.5 1.2 2.1 6.8 3.1 8.9 2.0 All dimensions in m Transparent ‘chin’ window to aid landing High rotor and fairing Partially exposed engine Innovative T-bar flight controls used by Robinson helicopters Innovative BERP rotor blade 0.0000 0.0500 0.1000 0.1500 0.2000 0.2500 0 500 1000 1500 2000 2500 3000 3500 х х х х w = 25 kg/m 2 w = 20 kg/m 2 w = 15 kg/m 2 w = 10 kg/m 2 kg Fuel weight ratio, R F Gross weight 850 0.139 Parametric analysis General layout of concept helicopter Estimated acquisition cost: $283,928
Transcript of Conceptual Design of a Low-Cost Training Helicopter
Conceptual Design of a Low-Cost Training Helicopter
Objective of Thesis • To design a concept helicopter that is low in cost and suitable for training
Research Approach • Use a set of performance requirements to conduct parametric analysis
and determine possible design configurations
Results • A concept helicopter was developed, and its performance and cost are
deemed to be comparable to existing market favourites
Benefits
• Incentivise labour market to increase pool of private-license pilots
• Reduce operating cost of companies that conduct in-house pilot training
Future Work • Update weight estimation equations used in the parametric analysis
• Assess performance and cost of British Experimental Rotor Program (BERP) rotor blade
• Assess performance and cost of diesel piston engines
Author: Liu Jianlin
Thesis advisor: Jack A. Stockford
Components Parameter Specifications
Main rotor
Radius 4.4 m
Tip speed 213 m/s
Solidity 0.036
Chord 0.25 m
Number of rotor blades 2
Airfoil NACA 0015
Direction of rotation Anti-clockwise (view from above)
Tail rotor
Radius 0.792 m
Tip speed 213 m/s
Solidity 0.0996
Chord 0.124 m
Number of rotor blades 2
Airfoil NACA 0015
Direction of rotation Bottom blade advancing
Engine Type Reciprocating (Lycoming O-360)
Power at sea level 134.2 kW
Fuselage Length 6.36 m
Width 1.2 m
Landing gear Type Fixed skids
8.8
1.6
0.5 1.2 2.1
6.8
3.1
8.9
2.0
All dimensions in m
Transparent
‘chin’ window to aid landing
High rotor and
fairing
Partially exposed
engine
Innovative T-bar flight controls used by
Robinson helicopters
Innovative BERP rotor blade
0.0000
0.0500
0.1000
0.1500
0.2000
0.2500
0 500 1000 1500 2000 2500 3000 3500
хх
х
х
w = 25 kg/m2w = 20 kg/m2w = 15 kg/m2w = 10 kg/m2
kg
Fuel weight
ratio, RF
Gross
weight 850
0.139
Parametric analysis
General layout of concept helicopter
Estimated acquisition cost: $283,928
