Transcript Fluidic thrust vectoring electric demonstrator Introduction • The FTV demonstrator will be based on the Vector II EDF aircraft • An Electric ducted fan model.

Fluidic thrust vectoring electric
demonstrator
Introduction
• The FTV demonstrator will be based on the Vector II EDF
aircraft
• An Electric ducted fan model allows similar characteristics to
a jet engine to be evaluated without dealing with hot gas and
related health safety issues
• This aircraft has been selected as the most suitable candidate
for the FTV modifications due to its prominently mounted engine
and suitable flight characteristics
Vector II specification
•Cruise Speed - 30m/s
•Wing Span - 1.16m
•Weight - 2.25Kg
•EDF Propulsion
•Power = 1.04KW
Flight Duration (battery life) = 8.5mins
Thrust = 22N
Propulsion Weight Total = 918g per E
unit
Overall propulsive system thrust to
weight of around 2
Simultaneous blowing
Sizing diagram
100
A
90
Secondary flow velocity < Primary flow velocity
Secondary flow entrained into primary,
contributes to the overall thrust
70
60
50
Vector II
40
B
0.9kg Modifications
30
Increase wing
area by 0.12m2
20
Recommended wing loading range
for R/C aircraft
10
0
45
55
65
75
85
95
105
C
Wing loading (N/m^2)
Primary flow entrained into the secondary flow
and vectoring achieved
Primary flow
Secondary flow
High aspect ratio nozzle
• High AR required to achieve
efficient vectoring
Secondary flow velocity > Primary flow
velocity
Resultant flow
0.5
Experimental force data
0
• Pressure losses minimised by
using constant area duct with
divergence angle constraints
• Design techniques:
Electric turbo-charger supplying secondary flow
Wemotec EDF providing primary flow
At cruise thrust of 6N, 1.5N of control force
achievable using low power battery supply
• ProE
20
40
• Glass fibre/epoxy resin
(Balsa/foam mould)
• Rapid prototyping ABS plastic
80
100
-0.5
-1
-1.5
Primary Thrust
0N
6N
6N repeat
7.75N
Conclusion
Ken Gill
Dr W. J. Crowther
Power, W
• The FTV seed corn demonstrator will be a modified off the shelf EDF kit
implementing the FTV technologies to rapidly de-risk the fluidic flight controls.
• Experience has been gained in designing and manufacturing axi-symmetric
to high aspect ratio nozzles
• The project has identified some implementation issues when applying bench
top hardware to flight hardware
• The project will highlight flight control issues concerning the use of an
integrated propulsion and pitch control system
Contact details:- [email protected]
Supervisor:-
60
-2
•Manufacture techniques:
Name:-
FTV, NFz, N
FzF, N
0
University of Manchester School of Engineering
INTEGRATED PROGRAMME IN AERONAUTICAL
ENGINEERING
The University
of Manchester
Power loading (W/N)
80