26-07-2012, 02:30 PM
DESIGN AND MODIFICATION OF AIRBUS A330-200
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INTRODUCTION
Designing is a process of usage of creativity with the knowledge of science, where we try to get the most of the best things available and to overcome the pitfalls the previous design has. It is an iterative process to idealism towards which everyone is marching still.
Design of any system is of successful application of fundamentals of Physics. Thus the airplane design incorporates the fundamentals of Aerodynamics, Structures, Performance and Stability & Control and basic Physics. These are based on certain degree of judgment and experience. Every designer has the same technical details but each design retains its own individuality and the mode of the designer.
Here the preliminary design has been done of an Commercial Passenger Aircraft. The basic requirements are the safe, comfortable and economic transport mode with reasonable time period of flight. Here comfort and safety are given primary importance.
Here the most possible considerations have been taken. And the flight parameters and limitations are studied.
The modern day calls for the need of latest aircrafts for the use of passenger transport which aims mainly at improving the aerodynamic characteristics as well as the passenger comfort. This design project also looks at the above aspects in a lot more closer way. Also the design project has been classified into different stages for easier approach and achieving better performance.
AIRBUS A330 –200
The A330-200 is the shorter-fuselage variant of Airbus’ A330 twin-engine widebody family, and has the versatility to cover all ranges from short-haul to true long-haul, with ideal sizing for point-to-point operations.
Its optimised 222-inch fuselage cross-section – which is shared with the other members of Airbus’ A330/A340 Family – accommodates 253 passengers in a comfortable two-class cabin layout that provides more window and aisle seats in much quieter cabins
Another advantage of the A330-200’s fuselage is its large-capacity underfloor cargo holds, which accommodate industry-standard LD3 containers in side-by-side loading. The A330-200 is well established with major carriers around the world, and has become a preferred aircraft for charter and leisure operators, as well as the growing low-cost long-haul market segment. With Airbus commonality in cockpit and cabin systems, an increasing number of airlines that fly the single-aisle A320 Family are discovering the advantages of stepping up to the widebody A330-200 for higher-capacity, longer-range service.
Tactical and Technical Data
The development cycle of the tactical-technical requirements is carried out on the basis of the analysis for a statistical material consists in additions given TTR for the projected airplane.
For passenger airplanes it is necessary to appoint number of passengers , altitude of cruising flight and cruising speed . For all types of airplanes distance or range and take-off distance must be established.
For all types of airplanes, resulting from their purpose it is necessary to choose number of crew members . For passengers airplanes stewards must be included into crew members. The number of stewards is determined from the conditions: two stewards for compartment of the first class with number of passengers up to 30, one steward for 50 passengers in cabins of the second and third classes.
Altitude of cruise flight (Hcr)
Usually a long range passenger aircrafts have altitude range of 10 to 13km from the ground level. In our project, the aircraft has the capacity of 380 passengers and range of 15000km with full payload. In the prototype (Airbus A330-200) the aircraft have the range of 13000km with full payload. So if it increases to 15000km, then we have to provide with reduction of weight of the flight or increase the fuel capacity with much more powerful engines. According to the dimensional and aerodynamic characteristics, it is better to increase the fuel capacity with much powerful engines to increase the range. The design aircraft should have same passenger capacity of that of the prototype, so the payload is not changed. The new design aircraft has 3 engines, compared to the prototype, 1 engines is more in the design aircraft. That will provide the necessary thrust required for the increment in the range.
Engines
Engine selection for each aircraft is depending on individual performances of each aircrafts. Mainly on how much thrust or power we need for the aircraft to have a safe journey and for all extra performances.
In our project we are selecting the engine General Electric CF6-80C2D1F according to static’s data of the aircraft. Three of these engines are used. Two are placed on the wing on both sides and one is placed on the top of tail section of the fuselage.
Engine positioning on the aircraft is also important as choosing an engine for the aircraft. Positing of engine is depending on the positioning of other structural elements of the aircraft.
DETERMINATION OF THE AIRPLANE TAKE-OFF MASS
The first step in the design of a new aircraft is to obtain an estimate of the take-off weight. This estimate is one of the crucial, since it is used in many other parts of the design. The total take-off weight is divided into fuel weight, payload weight, empty weight and etc.
The payload is further divided nonexpendable and expandable types. The nonexpendable payload remains unchanged throughout the flight plan. This includes the crew, passengers, baggage, revenue cargo, etc. Expendable payload is dropped somewhere in the flight plan, before landing. In this our project, we are constructing a passenger aircraft, so we have to consider it as a nonexpendable category.
The percentage that each of expendable and nonexpendable weights contributes to the total take-off weight depends on the mission or design objectives. Like longer range aircraft devote a greater percentage of their take-off weight to the weight of fuel.