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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:

  1. Boost Accelerometer
  2. Drag Accelerometer
  3. Transverse Accelerometer
  4. Normal Accelerometer
  5. Pitch Angular Accelerometer
  6. 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:

  1. Boost Accelerometer
  2. Drag Accelerometer
  3. Transverse Accelerometer
  4. Normal Accelerometer
  5. Pitch Angular Accelerometer
  6. Separation Indicator
  7. Pitot Pressure
  8. Yaw Angular
  9. Roll Rate
  10. Instrument Bay Temperature
  11. Temperature at Sting
  12. Angle of Attack (d)
  13. Angle of Sideslip (B)
  14. Static Pressure (on probe)
  15. 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:

  1. Boost Accelerometer
  2. Drag Accelerometer
  3. Transverse Accelerometer
  4. Normal Accelerometer
  5. Pitch Angular Accelerometer
  6. Separation Indicator
  7. Yaw Angular
  8. Roll Rate
  9. Angle of Attack (d)
  10. 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

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[DAVID EWART COLLECTION] [PICTON RANGE] [C.A.R.D.E.] [VIDEO]

Report Courtesy A.V.Roe Heritage Museum.

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