ARC Search Pics

Avro Arrow Specifications

Arrow Specs

banner

Some tech scans from Avro Documents.

Description Dimensions and General Data    

 

GENERAL DESCRIPTION

1 The Avro ARROW 1 is a delta wing supersonic, high altitude, all weather interceptor. The first aircraft is powered by two Pratt & Whitney J75 P3 gas turbine engines which are of the twin spool compressor type with afterburners. Subsequent aircraft will be powered by two J75 P5 series engines. Each engine of both series develops a military rated thrust of 15,500 pounds and a maximum thrust of 23,500 pounds.

2 The crew of two, a pilot and a navigator, are accommodated in separate cockpits arranged in tandem. Each cockpit is enclosed by a clam-shell type canopy which is normally opened and closed electrically. An explosive cartridge system is employed to open the canopies in an emergency. The cockpits are equipped with Martin-Baker C5 ejection seats to enable the crew to abandon the aircraft. Firing of the emergency canopy system and seat ejection are interconnected and require only one operation.

3 The airframe is of all metal stressed skin construction. The structure is an integral assembly with centre and inner wing torsion boxes forming the basis of the structure. The vertical stabilizer is secured to the centre torsion box. The inner wing torsion box skins are machined from the solid and the outer wing skins are taper rolled. The engines, duct bay, engine bay and rear fuselage are suspended from the inner wing to provide flexibility to the structure.

4 The aileron, elevator and rudder flying control surfaces are operated by a duplicated hydraulic system which powers control surface actuators. A damping system stabilizes the aircraft in all three axes, and also provides automatic rudder co-ordination. Provision is made for three modes of control, Normal, Automatic and Emergency. Hydraulic power is required for all three modes.

5 in the normal mode of control, forces applied to the control column by the pilot are converted to electrical signals which control electro-hydraulic servos. The movement of these servos is transmitted through the mechanical system to control the aileron and elevator hydraulic actuators.

6 In the automatic mode control signals to operate the electro-hydraulic servos can be originated by a ground station, or from the aircraft fire control or automatic navigation systems .

7 In the emergency mode, movement of the control column is boost assisted and transmitted by the cables to control the aileron and elevator actuators. Yaw damping and automatic rudder co-ordination only are retained in this mode.

8 The air conditioning system uses air tapped from the engine compressors. The air is cooled by air-to-air, and air-to-water heat exchangers, and by an air turbine and fan unit. The system supplies conditioned air to pressurize the cockpits. It also supplies conditioned air to the electronic equipment and the armament bay to maintain them at an operational working temperature. An emergency ram air supply provides cooling air to the essential equipment in the event of failure of the main system.

9 A low pressure air system supplied by air from the air conditioning system provides air pressure for the inflation of canopy seals, the instrument pack seals and the pilot and navigators anti-'g' suits.

10 Fuel is carried in twelve integral wing tanks and in two rubber cell type tanks in the fuselage. One of the tanks in each wing acts as a collector tank and fuel is pumped to the engine by a mechanically driven booster pump mounted in each collector tank. Fuel is transferred to each collector tank through a flow proportioner unit, from the wing tanks by air pressure, and from the fuselage tanks by a combination of air pressure and electrically driven transfer pumps.

11 The tanks in the RH wing and the front fuselage tank normally feed the RH engine, and the tanks in the LH wing and the rear fuselage tank, the LH engine. Provision is made for crossfeeding.

MISSING PAGE

FIXED DIMENSIONS AND GENERAL DATA
CHARACTERISTICS: ARROW 1 and ARROW 2
Length of aircraft (excluding probe) (77 ft 9.65 in)
  (76 ft 9.65 in)
Height of aircraft over highest portion of fin 21 ft 3.0 in
Ground angle (Angle between aircraft reference line and ground static line) 4.55 degrees
Tread of main wheels 25 ft 5.66 in
Wheel base 30 ft 1.0 in
   
WINGS:  
Wing area (including ailerons, elevators and 390.5 sq ft of fuselage and not including 28.63 sq ft of extended leading edge) 1,225.0 sq ft
Span 50 ft 0.0 in
Chord-Root 45 ft 0.0 in
       -Construction tip 4 ft 4.98 in
Mean Aerodynamic Chord 30 ft 2.61 in
   
   
   
   

The landing gear is of the hydraulically-actuated- tricycle type, with the main gear retracting inward and forward into the inner wing. The steerable nose gear retracts forward into the front fuselage.

The landing gear, wheel brakes, nosewheel steering and speed brakes are actuated by a 4,000 psi utility hydraulic system. A compressed air system is available for emergency lowering of the landing gear. The fully powered and irreversible flying control surfaces are operated by a separate 4, 000 psi hydraulic system consisting of two completely independent circuits.

Power for the electrical system is provided by two engine-driven alternators with constant speed drives for alterating current, and two transformer-rectifiers for conversion to direct current.

Where necessary space in the radar nose and weapon bay is utilized for test equipment and instrumentation to enable the development aircraft to carry out their designated role as flight test vehicles.

The external configuration of the ARROW 2 is basically the same as that of the ARROW 1. However, there are major internal differences, namely the weapon pack carrying four Sparrow 2D air-to-air guided missiles, installation of the ASTRA 1 electronic system, and replacement of the J75 engines with Orenda Iroquois engines. Provision is made for a jettisonable external fuel tank, and the mechanical proportioner type fuel system used for centre of gravity control on the ARROW 1 is replaced by an electrically controlled sequencing system.

--------------------------------------------------------------------------------

Previous Toc
Previous Toc


Wingspan: 50 feet
Lenght: 85 feet 6 inches
Height: 21 feet 3 inches
Weight (empty) 43 960 pounds
Weight (max take-off) 62 430 pounds
Cruising speed: 701 mph (Mach 1.06)
Max speed: 1 312 mph (Mach 1.98)
Climbing speed(0 to 50 000 feet) 4 minutes 24 seconds
Operating ceiling: 58 500 feet
Interception ceiling: 75 000 feet
Powerplants: 2 x Pratt Withney J-75 rated at 23 450 pounds each
   

--------------------------------------------------------------------------------

CHARACTERISTICS

ARROW 1 and ARROW 2

Air. - Foil section - Inner wing profile - Outer wing profile

Camber

Incidence - At root

- At construction tip Anhedral of chord plane Aspect'ratio

Taper ratio

Thickness ratio - parallel to Ch, Sweepback at 25% chord

of aircraft

NACA - 0003. 5-6-3. 7 (Modified) NACA - 0003.5-6-3.7 (Modified) NACA - 0003. 8-6-3. 7 (Modified) .0075 (Modified)

Zero degrees Zero degrees 4.0 degrees 2.04

0.0889

3. 5 and 3. 8 55 degrees

AILERONS:

Aileron area (aft of hinge line) - Total Span

Chord (average percent of wing

chord) - Root

ELEVATORS:

Elevator area (aft of hinge line) - Total Span

Chord (average percent of wing chord)

_ Tip Vertical tail area (including rudder) Span

Chord Root Construction tip Mean aerodynamic chord Airfoil section

- Root

NACA

Aspect ratio Taper ratio Thickness ratio (parallel to aircraft datum) Rudder area (aft of hinge line)

Rudder - Span (average)

- Chord (average percent vertical fin chord)

SPEED BRAKES:

Speed brake area (2) - Projected Span (each)

Chord

66. 55 sq ft 10 ft 0.0 in 25. 735

35. 0

106. 90 sq ft 10 ft 2. 0 in 14. 109 25.735

158. 79 sq ft 12 ft 10. 5 in 19 ft 0. 0 in., 5 ft 8. 0 in

13 ft 6.41 in 0004-6-3. 7 ( Modified)

Sweep Back - Leading edge59. 34 degrees

- Trailing edge 33. 08 degrees

- 1/4 chord 55. 0 degrees

1.04 0.2982 4.0%

38. 17 sq ft 9 ft 11. 0 in

14. 37 sq ft 2 ft 1. 08 in 4 ft 1. 0 in


--------------------------------------------------------------------------------

Previous Toc

Previous Toc


--------------------------------------------------------------------------------

LEADING PARTICULARS

FU EL SYSTEM Tank Capacities

TANK NO. OF CAPACITY OF TOTAL VOLUME OF

NO. TANKS EACH TANK USABLE FUEL

1 Fuselage 1 308 imp 370 US gal 263 imp 316 US gal

2 Fuselage 1 307 imp 371 US gal 259 imp 311 US gal

3 Wing 2 165 imp 198 US gal 302 imp 362 US gal

4 Wing 2 101 imp 121 US gal 180 imp 216 US gal

5 Collector 170 imp 204 US gal 292 imp 350 US gal

6 Wing 176 imp 211 US gal 308 imp 370 US gal

7 Wing 2 322 imp 386 US gal 558 imp 670 US gal

8 Wing 2 207 imp 248 US gal 346 imp 415 US gal

TOTAL FUEL CAPACITY 2, 508 imp 3,010 US gal 19,562 lb.

Tank Pressure - Wings 25 psia (initial flights 1st aircraft)

19 psia (subsequently)

- Fuselage 10 psi differential (initial flights 1st aircraft)

7. 5 psi differential (subsequently)

Pressure Refuelling One point in each wing

ENGINES

Designation Pratt and Whitney J75 P3 (1st aircraft)

J75 P5 (subsequently)

Twin spool axial flow gas turbine with

afterburner

Fuel specification 3GP-22B-1 Ref 34A/159

MIL-F-5624 Grade JP4 CU. S. )

D. Eng R. D. 2486 (U.K.)

F. 40 (NATO Symbol)

Oil specification MIL-L-7808C Ref 34A/226

C-148 (NATO Symbol)

Oil tank capacity 5. 5 gal U.S.

Usable Oil 3. 5 gal U. S.


--------------------------------------------------------------------------------

Previous Toc

Previous Toc


--------------------------------------------------------------------------------

ACCESSORIES GEARBOX

Manufacturer Sargeant Engineering

Accessories gearbox to engine ratio 0. 823:1

Engine starter to engine ratio 0. 823:1

Oil specification As for engines

Gearbox oil capacity 1 gal. imp

MAIN LANDING GEAR

. Type

Manufacturer and model

Track

Shock absorber Fluid specification Recuperator

Whe e is Tires < Inflation pressure Brakes

Hydraulically retracted with twin wheels in tandem

Dowty - XV 1283-1A LH XV 1283-1B RH 25 feet 9 inches static

25 feet 7. 6 inches touchdown

Dowty liquid spring with recuperator Dowcan 200 silicone fluid

Dowty - V 1283-6A LH V 1283-6B RH Goodyear

Goodyear 29 x 7.7 Type VII tubeless 255 psi

Goodyear hydraulically operated

NOSE LANDING GEAR

Type

Manufacturer and model Shock absorber

Fluid specification Wheels

Tires

Inflation pressure

Hydraulically retracted, steerable twin wheeled unit

Jarry Hydraulics 1500 Dowty liquid spring Dowcan 200 silicon fluid Dunlop

Dunlop 18 x 5. 5 Type VII tubeless 170 psi

UTILITY HYDRAULICS

Fluid specification

Pumps (2)

Pressure regulator setting Reduced pressure Accumulators System (1)

Emergency brakes (2) Return surge damping Compensator (1)

Compensator capacity Emergency Nitrogen System Manufacturer

Charging pressure Bottle capacity (1)

3GP-26A Ref 34A/ 100 MIL-H-5606A (U.S.) D.T.D. 585 (U.K.) H-515 (NATO Symbol) Vickers constant delivery 4200-4250 psi

1500 psi 200 cu. in. 110 cu. in. 60 cu. in. Loud

5 gal. imp.

Walter Kidde 5000 ps i

300 cu. in.


--------------------------------------------------------------------------------

Previous Toc
Previous Toc


--------------------------------------------------------------------------------

FLYING CONTROL HYDRAULICS

Fluid specification Pumps (2 each system) Pump pressure Reduced pressure Accumulators System (1 each system) Return surge damping (1 each system) Booster circuit

(1 each system) Compensators (1 each system) Compensator capacity

As for utility hydraulics Vickers variable delivery 4000 psi

1250 psi

Self displacing 100 cu. in. 60 cu. in.

25 cu. in.

Loud dual pressurized 5 gal. imp.

EJECTION SEATS - 2

Liquid oxygen converter (1) Converter capacity Regulators (2)

Supply pressure to regulators Emergency Oxygen System Bottles (?.) gaseous

Bottle capacity Charging pressure

Aro Equipment Corp. 5.0 litres

Firewell F 2400 - 11C 70 psi

Walter Kidde 50 cu. in. 1800 psi

FIRE EXTINGUISHER SYSTEM

Bottles (2) Extinguishant Capacity of each bottle Nitrogen pressure

Walter Kidde Freon 12B2 12 lb

400 psi at 70 OF

ENGINE DE-ICING

Type

AIRFRAME DE-ICING

Hot air bleed from compressor

Pilot's windshield and side panels Engine intake and ramp

Electro-thermal Electro-thermal

ELECTRICAL SYSTEM AC

Constant speed unit Alternators

General Electric Lucas Rotax

115/200 volts AC. 400 cycles 3 phase


--------------------------------------------------------------------------------

Previous Toc

Previous Toc


--------------------------------------------------------------------------------


7f1I-I314-1

interconnected by frames and covered by an upper and a lower skin. Each speed brake is pivoted independently at the forward end on two hinge pins and is actuated by a jack enclosed in a sealed compartment in the duct bay. See fig 13.

53 The forward faces of the two floating duct sections are connected to the ducts in the centre fuselage by flexible joints which are sealed by rubber 'O'-rings. The aft end of each duct is supported by two IV' struts from the inner wing and is located laterally by a turnbuckle from the structure. The joint between the aft end of the duct and the engine tunnel is sealed by a sheet rubber seal.

54 Twenty-four gills, spring-loaded tothe open position are fitted to the inside of each duct in line with the engine adaptor ring. See fig 14. For operation of the cooling gills see Arfow 1 Service Data - Engine Installation.

IG. 13 SPEED BRAKE ATTACHMENT

and a IV' support , strut at station 538.77. It is attached to the centre fuselage bulkhead at station 485 and the engine bay frame at station 591. 65. The bay houses two floating sections of the engine air intake ducts and two speed brakes. It consists of a main frame, four longerons and twenty intermediate frames >> red by an outer skin.

50 The upper longe rons connect with the lower longerons of the centre: fuselage and terminate at the main frame at silation 5313.77: The two lower longerons are connected to bulkhead 485 at the instrument pack rear attachment points and extend the full length of the duct bay to connect with the engine bay main frame at station 591.65.

51 Two longitudinal beams, inboard of the speed brakes connect the bulkhead at station 485 to the main frame at station 538. 77 and form the main members for the speed brake inboard hinges and the speed brake actuating jack r-tachments. The support hinges securing the ~_~t bay to the inner wing are sealed by a stain= less steel seal.

GILL SPRING TUNNEL FAIRING ENGINE TUNNEL

FLOATING DUCT

FLEXIBLE SEAL-DUCT TO TUNNEL

HEAT EXCHANGER AIR OUTLET

TIII-1313-1

5Z Each speed brake.eonsistr of two beams,

FIG. 14 ENGINE BAY COOLING GILLS

 

AVIATION TOP 100 - www.avitop.com Avitop.com

ONLINE STORE FEATURED ITEM:


| HOME | STORE | NEW INFO | CONTACT US | ABOUT US |

© C© Copyright AvroArrow.Org, 2009. Materials may be freely copied and distributed subject to the inclusion of the copyright notice, and credit must be given to AvroArrow.Org. The site is intended for historical and informational purposes. This site contains links to other Internet sites. These links are not endorsements of any products or services in such sites, and no information in such sites has been endorsed or approved by this site.

WEB SITE HOSTING PROVIDED BY CAPITOL TECHNOLOGIES

 

ARC Logo Strip