1. MECHANICAL SYSTEMS OF CONCORDE
PRESENTED BY :
Vishak CJ
Gec Thrissur
530 PE

2. INTRODUCTION
After the World War II, Great Britain realized the necessity for faster civil planes and created the De Havilland D.H. 106 Comet, the first commercial plane with jet engines. During the 50's a committee was formed involving representatives from airlines, aircraft industries, engine industries and government employees to discuss an advanced design.
There were 3 possible innovative designs that could be followed.
The first was a plane with a very strange wing, -M shaped, with max speed 1.2 Mach.
The second design was the one that was similar with the final Concorde, with similar wing but with max speed 1.8 Mach.
The third one was chosen from the Americans and was for a huge plane with max speed 3 Mach.

3. The engines used afterburners, which are necessary for the plane to obtain supersonic speed.
An agreement was signed between the Britain and france for developing the plane.
The Olympus Mk 593B engine was used .
The aircraft used very complicated systems that were not used before.
France was constructing the 60% of the fuselage and wings, because Britain provided the engines.
When put into service The Concorde became very expensive to use with increasing oil prices . The end of Concorde era was just a few years back . The advance in aeronautics that it brought was enormous although its service life was short .

4. TECHNICAL SPECIFICATIONS
DIMENSIONS
PERFORMANCE
WEIGHTS
POWERPLANT
DROOP NOSE
FUELSYSTEM
DELTA WING
LANDING GEAR

5. DIMENSIONS

7. PERFORMANCE Maximum Operating Cruise Speed -Mach 2.04 (around 1350MPH)
Maximum Permissible Range Miles
Average Take-off speed -250MPH
Average Landing speed -185MPH
Maximum operating altitude -60,000Ft
Maximum Oil temp for start and takeoff- 125 Degrees Celcius
Maximum Oil temp Continuous operation- 190 Degrees Celcius

8. WEIGHTS Max Weight Without Fuel (Zero fuel weight -(92,080 kgs)
Max Payload - (13,380 kgs)
Max Take Off Weight - (185,000 kgs)

9. POWERPLANT Engine Model : Olympus 593 Mrk610 turbojet
Engine Manufacturer : Rolls-Royce/SNECMA
Number fitted : Four
Maximum thrust produced at take off, per engine -38,050 lbs (170 KN) (with afterburner reheat in operation)
Maximum thrust produced during supersonic cruse, per engine -10,000 lbs
Reheat contribution to performance- 20% at full thrust during take-off
Fuel Type- A1 Jet fuel
Fuel Consumption (at Idle Power) kgs/hr .
Fuel Consumption (at Full Power) kgs/hr .
Fuel Consumption (at Full Re-heated power) kgs/hr .

10. ENGINES
Roll-Royce provided the development of the Olympus engines while SNECMA developed the exhaust and reheat system. A total of 38,050Lbs thrust were available.
The Olympus engines are 2 spool engines. The inner shaft revolves within the outer shaft. The engine consists of 14 compressor stages, 7 on each shaft, driven by their respective turbine systems. At supersonic speeds when the air approaches the combustion chamber is is very hot due to the high level of compression of 80:1.

11. ENGINES
To protect the later compression stages the last 4 stages are constructed of a nickel-based alloy .The RPM of the engine's outer shaft is controlled by the amount of fuel being burnt. By varying the surface area of the primary nozzle, the inner shaft RPM can be controlled relative to the outer shaft RPM.
Concorde is the only civil airliner in service with a 'military style' afterburner system installed to produce more power at key stages of the flight. This reheat system, injects fuel into the exhaust, and provides 6,000Lb of the total available thrust per engine at take off. This is used on take off and is what is mainly responsible for the additional noise that Concorde makes. The reheats are turned off shortly after take off .
The Aircraft has an electrically controlled throttle system that is used to control the power delivered from the engines .The computer applies the power to the engines in a correct and controlled manner.

12. ENGINES
The engines also have ratings where they can be selected to different power or rating settings for different parts of the flight. eg take off or cruise. A contingency setting is available for use during engine failure and more power that normal is required from the remaining engines
in the second photo, the afterburner (reheat) system can be clearly seen, it is the smaller ring structure situated inside the engine casing

13. AIRFLOWS AND INTAKES
To further improve engine system performance, the air flow through the engine area is changed at different speeds via a variable geometry intake control system .
The air intake ramp assemblies main job is to slow down the air being received at the engine face to subsonic speeds before it then enters the engines. At supersonic speeds the engine would be unstable if the air being feed to it was also at a supersonic speed so it is slowed down before it gets there.
SUBSONIC SPEEDS(TAKEOFF & CRUISE)
At take off the engines need maximum airflow, therefore the ramps are fully retracted and the auxiliary inlet vane is wide open Shortly after take Off the aircraft turns off re-heats and the power is reduced.
The secondary nozzles are opened further to allow more air to enter, therefore quietening down the exhaust. The Secondary air doors also open at this stage to allow air to by pass the engine

14. At take off and during subsonic flight, 82% of the thrust is developed by the engine alone with 6% from the nozzles and 21% from the intakes
During the Supersonic cruse only 8% of the power is derived by the engine with the other 29% being from Nozzles and an impressive 63% from the intakes.
Supersonic cruise : At the supersonic cruse speed of mach 2.0 the ramps have moved over half their amount of available travel, slowing down the air by producing a supersonic shockwave (yellow lines) at the engine intake lip.

15. DROOP NOSE
POSITION 1 :Nose and Visor fully retracted in up position Used during Supersonic cruise and when parked
POSITION 2 :Nose fully up, Visor retracted into droop nose Used during short subsonic cruise (eg fly past) and windscreen cleaning
POSITION 3 : Nose down at 5 degrees Visor retracted into droop nose Used for take off and taxi
POSITION 4 : Nose down at 12.5 degrees up, Visor retracted into droop nose Used for landings and taxi, although raised quickly to position 3 to avert damage

16. FUEL SYSTEMS
It has multiple fuel tanks . The only difference is that during flight fuel is transfered from tank to tank to maintain trim and balance of the aircraft . The Center of Gravity is critial and required to be moved for different speeds. The fuel is also used as a heat sink for cooling purposes .

17. DELTAWING
Unlike a regular aircraft with over 50 moving parts on wings a concorde has only 6 of them .
The design gives good lift at low airspeeds by increasing the angle of attack and it also performs at high speeds with very little drag.
As the aircraft gets closer to the ground, the downwash of the air between the wing and the ground creates a cushion . Hence landings are smooth.
For accurate weight and strength a copper based aluminium alloy called RR58 was used for this purpose . The process used was called sculpture milling .
Due to the process there was no welds or rivets anywhere on the wing ; hence strength was improved and about 700 pounds of material was saved .

18. LANDING GEAR
Concorde has a tricycle landing gear layout, with a nose gear and 2 main gear. Separate from this configuration is a tail bumper gear that is fitted to prevent any damage to the fuselage
The nose gear is situated behind the flight deck, making taxing different to a normal aircraft and it also retracts forwards.
The main landing gear on Concorde was the first to be fitted with the now standard Carbon Fibre brakes that are seen on all aircraft today

19. LANDING GEARS MAIN LANDING GEAR: Manufacturer- Messier-Dowty
Number of wheel on each bogie- 4
Operation- Hydraulics
Retraction direction- Inwards
Tyre type- Michelin NZG
Tyre pressure- 232PSI
Brakes -4 X Dunlop Carbon Fibre with anti-skid system

20. LANDING GEAR Manufacturer- Hispano Number of wheels- 2
Operation- Hydraulics
Retraction- direction Forwards
Tyre pressure- 190PSI
Brakes- None
Steering- Electrically signalled, Hydraulically controlled.
Steering angle- +/- 60 Degrees

21. thank you