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FFM-Technical Results
FREE
FLIGHT TEST MODELS:
Canadian
Armament Research Development Enterprise, were contracted
by Avro to conduct flight test model testing at the
Pt.Petre missile test range.
These test results were compiled from Avro Technical Report P/F.F.M./47,
a 75 page summary of free flight model tests.
OVERVIEW:
The
purpose of the free flight model testing was
to provide dynamic stability and control data
for the CF-105. Aerodynamic measurements of pitching,
yawing, rolling planes and aircraft drag were
required before the "Arrow" went into
full production. No prototype was built, test
data went directly to production design and implemented
on production aircraft.
Ground
launch testing was chosen over, air launch from
aircraft and ballistic firing from a large caliber
gun. The ground launch technique was chosen because
it would be a more consistent form of data retrieval.
" NIKE " JA
TO XM5 was the first successful booster rocket
produced in the United States. Standard design
was 262.45 kN (59,000 lbs.) of thrust. AVRO engineers
modified the boosters for selective needs. Boosters
were reloaded with a smaller charge to achieve
200.17 kN (45,000 lbs) of thrust. This modified
charge gave the boosters a burn time of 2.3 to
3.0 seconds. The top speed was between mach 2
and, 2.3. Where as a full charge would give a
top speed of over mach 3. The boosters used a
solid propellant. The models were usually released
at mach 1.7 as a rule. Avro modified the horizontal
fin assemblies to give optimum stability.
Each
scale free flight model had 2 FM transmitters
of 2 watts each, 218 m.c. and 224 m.c. frequencies.
Models were powered by silver peroxide-zinc lightweight
batteries, producing 6 volts at 10 amps and lasting
1 hour. The more advanced models had a commuted
duct pressure system, and up to 24 sensors.
There are
3 types of models, they are crude, drag and stability.
 Styles
varied as design progressed. 
Dimensions:      
Average
mass:
217
kg
478
lbs
Length(w/o
antenna):
2794
mm
9
ft. 2 in.
Antenna:
762
mm
2
ft. 6 in.
Wingspan:
1905
mm
6
ft. 3 in.
CRUDE:
FFM-1
Point
Petre Range 14 Dec.1954
Slab
wing, profiled fin.
INSTRUMENTATION:
Boost
Accelerometer
Drag
Accelerometer
Transverse
Accelerometer
Normal
Accelerometer
Pitch
Angular Accelerometer
Separation
Indicator
RESULTS:
-test
of booster/model combination: perfect
-problems
of tracking radar following the booster after
separation, and kine theodolite could only
follow the model for 1 second
-Normal
Accelerometer failed
 
 
FFM-2
Point
Petre Range 16 Dec.1954
Slab
wing, profiled fin.
-5
channel telemetry
-no
intake ducts
RESULTS:
-test
to confirm launch number 1
-same
kine theodolite tracking problem as in number
1 launch
-same
instrumentation as number 1, all functioned correctly
FFM-3
Point
Petre Range 12 May. 1955
Slab
wing, profiled fin.
-5
channel telemetry
-no
intake ducts
-yaw
impulse mechanism, device designed to fire small
charges from a hole in either side of the model
nose, every second 7.8lbs/sec
INSTRUMENTATION:
Boost
Accelerometer
Drag
Accelerometer
Transverse
Accelerometer
Normal
Accelerometer
Pitch
Angular Accelerometer
Separation
Indicator
Pitot
Pressure
Yaw
Angular
Roll
Rate
Instrument
Bay Temperature
Temperature
at Sting
Angle
of Attack (d)
Angle
of Sideslip (B)
Static
Pressure (on probe)
Static
Pressure (behind compensator cone)
 
RESULTS:
-failure
of yaw impulse system on this model
-data
sent to Bell Aircraft to reduce to aerodynamic
functions, also reduced by hand at Avro to check
Bell findings.
-kine
theodolite was able to track model for over 7
seconds but the radar failed to track the model
FFM-4
Point
Petre Range 14 June. 1955
Slab
wing, profiled fin.
-5
channel telemetry
-no
intake ducts
-yaw
impulse mechanism
INSTRUMENTATION:
Boost
Accelerometer
Drag
Accelerometer
Transverse
Accelerometer
Normal
Accelerometer
Pitch
Angular Accelerometer
Separation
Indicator
Yaw
Angular
Roll
Rate
Angle
of Attack (d)
Angle
of Sideslip (B)
RESULTS:
-yaw
impulse worked perfectly
-kine
theodolites were able to track for over 23 seconds,
assisted by puffs of smoke from the yaw impulse
system firing
-inaccuracies
in Bell data lead Avro to send all data to CARDE
for reduction to aerodynamic functions
 
Crude models
had fixed tab elevator at 1.5 degrees +.
>>CLICK
FOR PAGE 2<<
Drag
and Stability Models
Related
pages
[DAVID EWART COLLECTION] [PICTON
RANGE] [C.A.R.D.E.] [VIDEO]
Report
Courtesy A.V.Roe
Heritage Museum.
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