The A320 Is The First Launched Engineering Essay

The A320 Is The First Launched Engineering EssayIn this assignment, I was selected one elegant phone linecraft which is A320-200. Generally, the family of A320 consists are A318, A319, A320 and A321. I would like to prefer A320-200 because of the airmanshipcraft is better than some opposite variants. This aircraft was suffer as commercial passengers jet airliner by creasebus. The A320 is best-selling aircraft since launched and received a lot of order somewhat the being especially from Europe and Asia. The aircraft was designed a short body and narrow compared to a nonher variants. It also is competent to accommodate up to 220 passengers which are consists 150 seating in twain class cabin and up to 180 seating in racy density layout for a low cost. The advantage is this aircraft employ digital cut mound-by-wire assure systems. This system employ electronic interface to replaces the manual rush control. The transposition of the control systems are for protected air frame structural to obtain laid-backer safety, to contract buff workload and also to make aircraft stability and smoothness during escape of stairs.The A320 is the runner launched among the A320 family in March 1984. The first flight in 22 February 1987 and antedate by Air France in 28 March 1988. The A320 families typically use digital fly-by-wire control systems and control the aircraft by joystick at side-stick commonly on right hand side, in commercial aircraft. Since the introduction A320 family, Airbus industry gets many order form airliners in total 5 323 aircraft that gene grapple been delivered ahead August 2012. The first faster selling aircraft in the world had been recorded from 2005 to 2007. The development A320 by airbus industries are fit to compete with up-to-the-minute aircraft such as Boeing 737, 717, 757 and McDonnell Douglas MD-80.The range A320-200 usually is round 3 ccc nautical miles with 150 passengers on board. It is can accommodate up to 220 passengers and the electrical strength of cargo is about 37.41 m3. The aircraft length and wingspan which are 37.57 m and 34.01 m. A320-200 offered with a maximal fraudulence slant (MTOW) of 73 d kg, maximum set down weight of 64 500 kg, maximum zero sack weight of 61 000 kg and empty operating weight 42 century kg. The two engines used are CFMI CFM56-5s or IAE V2500s and the squash between 113 to one hundred twenty kN. The minimal journey animate that the aircraft can fly is about 811 km/h and the maximum cruise fastness is 875 km/h. The maximum cognitive content of terminate that able to accommodate is 53 699 kg. The more specification and prepare of this aircraft it shows in the table below.A320-200Fuselage width3.96 mFuselage height6 mFuselage length37.57 mCabin length27.51 mCabin width3.7 mCabin height2.13 mEmpty operating42 100 kg max Zero send away61 000 kg muck Takeoff Weight73 500 kgMax Landing Weight64 500 kgMax kindle capacity53 699 kgNormal cruise811 km/hMax cruise875 km/hMax ceiling12 131 mTake off field length2 158 mLanding field length1 899 mSeating capacity180Cargo capacity37.41 m3EnginesIAE V2500 serial publication orCFM International CFM56-5 seriesThrust111-120 kNThe specification of A320-200Pre-flightPreflight is the first sort onward they can touch off a journey. thither have several procedures in airport before the aircraft can charade. Preflight it also know as push back or taxi out. The aircraft is pushed backward away from the gates by tugs. Tug is vehicles that used to push the aircraft. After the aircraft get out from its gate, hence the aircraft move to racetrack return by taxiway. The movements of aircraft through taxiway at very let up speed and they require clearance before the aircraft make a movement. establish on this assignment, I have chosen one civil aircraft A320-200 and the culture of flight from origin Kuala Lumpur International airdrome to Jakarta Airport. Before flight, the maximum of dis patch must(prenominal) be calculated. on a lower floor is the computing maximum payload that the A320-200 is able to carry.Max Takeoff Weight (MTOW) 73 500 kgMax Landing Weight (MLW) 64 500 kgMax Zero Fuel Weight (MZFW) 61 000 kgDry operating(a) Weight 42 100 kgFlight blank space 1 144 kmMean speed 811 km/hFuel flow 2 600 kg/hReserve give the sack 13425 kgThe calculation of maximum payload that the aircraft is able to carryFlight era Flight give notice load during caper Payload during arrive Payload of MZFW As the aircraft can ope estimate safely, the utmost total payload base on that calculation is chosen. So, the maximum payload that the aircraft is able to carry is 8 975 kg.Take-offAfter calculated of maximum payload that the aircraft is able to carried, the aircraft leave alone hold on to takeoff. When the pilot ready to takeoff and approved clearance by Air Traffic Control, the aircraft may continue action by release the aircraft brake, prior the thrott le and development reasonably. The A320-200 required takeoff distance is about 2 158 m. The lift created because of movement of air through the aerodynamic wings exit produce difference pressure which the pressures below the wing get mellowed pressure than to a higher place the wings. When the aircraft reached takeoff speed within 180 mph and the higher pressure at below both of wings obtained, then the lift produce lead cause the aircraft can fly (also known as Vr). The aircraft fly until reach initial get on distance 35 feet.There are lots of factors that can be act on takeoff performance. Major factor is aircraft weight. The weight of the aircraft go forth effect on takeoff distance and the takeoff speed. Because of heavier weight, the aircraft require more lift drive to attaint fly by increasing the speed to produce high pressure at both wings. The limitation is set to batten down the aircraft is not overweight to operate safely. Before flight, make sure that the weig ht of aircraft no exceeds the maximum takeoff weight (MTOW). Based on the information of the aircraft, the organise already set the maximum takeoff weight is 73 500 kg.Temperature can be touch on takeoff performance. This is because the efficiency of engines it is seems on air temperature at contact. The high temperature can cause lower thrust generated by an engine. This happen because the totals draw off it is more nearly of the total thrust. So, the aircraft need long-lasting takeoff distance to attaint higher speed. At the origin airport, the temperature surrounding is about 30oC. That temperature is not too high so aircraft can takeoff with normal distance and speed.Flap setting also can be effect on takeoff performance. Because of flap setting give effect to aerodynamic drag. Usually, most of civil aircraft set the flap is about 10 to 15 degree during takeoff. The used of flap can reduce takeoff distance but increase in flap setting repayable to increase in drag. Increa se in drag will cliff the incline of rising slope. So the aircraft need longer fourth dimension to reach the train altitude. In addition, increasing takeoff distance will kick the bucket if the airframe soil by frost, ice or snow during takeoff and reduce takeoff performance.ClimbClimb is afterward takeoff phase. Climb is an ope symmetryn of aircraft increase the altitude until reach cruising level. Usually, commercial aircraft leaves the dry land with rate of wage increase 257km/h and at 15 degrees tends of rear. To ensure the aircraft climb with the shortest distance and time, the angle of climb and rate of climb must be calculate before flight. This is authoritative to know the angle and rate of climb to ensure the aircraft extremely get lift until reach cruising altitude with appropriate time and distance.The climb slope is the ratio of height gained to the horizontal distance traveled by aircraft. It is depend on vary thrust, drag and mess of aircraft. To ensure t he aircraft climb, the total thrust must be greater than total of drag. Thats hatch the aircraft can fly if the redundant thrust produce. Below is the calculation of climb gradient that I had been made in this aircraft. The thrust, drag and weight of aircraft are 49400 lb, 34580 lb and 162040 lb. enactment for climb gradient is (thrust drag) / weightClimb gradient (49400-34580)/162040 0.091The angle of climb is the angle between heights gained to the horizontal distance traveled by aircraft during climb. Below is the calculation for angle of climb. The formula of angle of climb tap of climb= sin-1 (thrust drag/weight)= sin-1 (49400-34580)/162040)= 5.22The rate of climb is the vertical component of the speed, convey in feet per minute. It depends on the airspeed (V) and the angle of climb or climb gradient. The rate of climb is strategic to ensure aircraft reach cruising altitude in the shortest time. Below is the calculation for rate of climb. The information is same with the calculation in above and the velocity of the aircraft is 438 knots. The formula in this calculation is V x (Thrust Drag) / Weight. calculate of climbROC = V (thrust drag/weight)ROC = 438 (49400-34580)/162040)ROC = 39.86 canvasCruise is a phase where the aircraft pass through the climb phase and ends when the aircraft derivation for landing is initiated. Cruise also define where the flight journey are between climb and affinity phase. Cruising altitude is determine by the pilot refer to flight planned and approved by air craft control. After aircraft reached cruising altitude, the pilot may decrease the power to reduce fuel consumption and economize the flight level. To maintain the flight level, the fall of lift is equal with the amount of weight. Mostly, the large aircraft fly around 35 000 ft and can be vary with the types of aircraft, length of flight, weather conditions, air turbulence and the location of some other aircraft in the air. The largest percentages of trip time and trip fuel are consumed typically in cruise phase. The amount of fuel burn and total time can change by speed of aircraft and altitude that pilot selected.There are three options to identify the best range cruise, speed cruise and the best endurance cruise. Range is defined as distances of journey depone on the amount of fuel available. The maximum range of an aircraft is possible distance depend the maximum amount of fuel can be inserted. specialised range is the range performance of the aircraft at a moment in time. The specific range of this aircraft calculated below given the total of fuel are 17 091 kg.Specific range = knot/fuel flow= 438/2600= 0.17= 0.17 17091= 2905.47 kmEndurance is the time that aircraft can remain airborne with the fuel available. It also defines as how long the time of an aircraft in the sky with the fuel available. It will be greatest when the fuel is used at the lowest possible rate. That mean the fuel flow used is marginal. Below is the cal culation of specific endurance.Specific endurance = flight hours/fuel flow= 1.41/0.72= 1.96 surrenderDescent is defined where an aircraft decrease the altitude. Aircraft dusk phase begin after an aircraft passed cruising phase and end when the aircraft draw close for landing phase. During race, the aircraft altitude decrease slightly by reduction the thrust and power. When the aircraft speed decrease will make less(prenominal) of lift. Thus the aircraft will lower their altitude until reach come up phase. The climb should be thrust greater than drag to produce excess thrust, but fly telephone line the aircraft drag must be greater than thrust to produce excess drag.To operated efficiency when descent, the sack up of descent betoken must be determine by flight crew to ensure that the aircraft is in correct level to start the descent phase. Top of descent read is a point at which the descent is initiated from the cruising level. Determine for top of descent point is based on the ratio 31 which means aircraft will require three nautical miles distance for both(prenominal) one thousand feet of aircraft altitude above ground. Based on this assignment, the flight level of that journey is 36000 feet. Refer to the ratio, 36000 feet is divided to 1000 equal to 36. consequently 36 are multiply by 3 equal to 108. That mean 108 NM is needed for fly descent to the ground.During descent, pilot must consider of the descent gradient, angle of descent and the rate of descent. This is most-valuable to reduce descent distance thus reduce fuel consumptions. Descent gradient is the ratio of height descended to distance travelled by aircraft. The amount of drag must be greater than thrust, thus excess drag is produced. The formula of descent gradient is (drag-thrust)/weight. The drag, thrust, weight of aircraft are 34580lb, 24206lb and 162040 kg.Descent gradient = (34580 24206)/ 162040= 0.064Angle of descent also important to control the descent angle by reducing engi ne power and pitch angle. The pilot should make sure that the angle is correct by determine the appropriate angle. The formula is sin-1(Drag- Thrust) / Weight.a = sin-1 (34580 24206)/ 162040= 3.67The rate of descent is the vertical component of the speed, expressed in feet per minute.It depends on the authoritative airspeed (V) and the descent gradient according the formula V (Drag Thrust) / Weight. The true airspeed of the aircraft is 438 knots. stride of descent = 438 (34580 24206)/ 162040= 28.032ApproachApproach also called final sexual climax or final leg begins several miles from the airport. Final procession starts after the aircraft passed descent and end when the aircraft nearest to the airport for landing. In this phase, the approaching aircraft require from air traffic control to control and separated the aircraft within the same theatre of operations either other aircraft leaves from airport or comes to airport. The appropriate aircraft speed for approaching abou t 121 knot to 140 knots to the ground. The operate smoothly when approach, the pilot must set the flap between 10 to 15 degrees and set all-inclusive flap when the aircraft close to land. This is important to increase the drag so the speed of aircraft will reduce, thus the altitude also reduce. Before aircraft touch down the runway, make sure that the landing gear lowered at about 5nm from the touch down. So that, landing gear will increase the drag and make aircraft slowest.Approach slope is path of the aircraft follow its final approach till landing on a runway. Approach slope basically as the aircraft path slightly downward slope. A commonly used approach slope is 3 from the horizontal. But they may vary steep approach paths at every airport where depending on topography, buildings, or other considerations. The term glide slope is often applied to mean approach slope although to be correct it applies to the vertical guidance element of the musical instrument Landing System.Lan dingLanding is the last part of the aircraft that return to the ground. It is a phase after an aircraft is passed through final approach. Landing phase begins from true height around 35 feet to 50 feet to the ground. Mostly, the aircraft landing with the speed around 190km/h relative to the ground until it touch down on runway. The separate of landing consist of airborne segment touchdown and ground roll which the point of aircraft stop on runway. When the landing gear touch the runway, the pilot may quickly do several actions by pulling back the throttles, position the spoilers, applying reverse thrust of the engine and applying the brakes. The spoiler used during landing is for sever airflow to reduce lift and create drag, thus the speed will reduce quickly. Where applying brake are to make aircraft stop with efficiently and less landing distance. Before aircraft landing, aircrew must make sure that the minimum landing distance is less than the distance runway available. Also i t is important to determine the weight of the aircraft in not exceed the maximum landing weight. Based on this assignment, the minimum landing distance require on this aircraft is about 1899 meter. The research that I have been made, the destination airport, Jakarta Airport has a distance runway 3600 meter on the runway 07R/25L. So, the aircraft is able to land safely on that runway. Other that, the weight of the aircraft is not transcend maximum landing weight which is the maximum landing weight of this aircraft is 64 500 kg.There are many factors that can be affected on the landing performance. The distance required for landing is related to aircraft ground speed on landing. Thus increased landing speed will give a significantly increased landing distance requirement. The aircraft mass also can effect of landing performance. This is because increasing the mass will reduce the deceleration force and thus increases the landing distance. However, the major effect is that the landing distance required will increase with increasing mass. oddmentAs a conclusion, mass and performance is related to each other to ensure the aircraft always in safe condition during operation. To generate safety, every flight profile must be a calculation before the aircraft start to fly. In preflight, calculation of maximum payload is very wideness to ensure aircraft is not overloaded. Serious problem occurs if the aircraft is overloaded such as need long distance to takeoff, poor performance and also may cause the aircraft stall when climb. In climb phase, calculation for angle of climb and rate of climb is important to get the best angle and speed for climb to be able aircraft reach the level altitude with minimum of time. When the aircraft reached level altitude or cruise, a calculation for range is important to get the best range of aircraft with the minimum of fuel consumption. With minimum of fuel burned, thus the aircraft will get the long distance and could save the economy. In descent and approach phase, require calculation to be determining what the angle and rate for descent and also the distance the destination. Minimum time is requisite to reach the airport and avoid congestion in air traffic while to perform safe operation. The analyzing that I had been made, the higher percentage of aircraft accidents occur due to human error. Thus, precise calculations required in every of flight phase to prevent accidents happens.BibliographyWebsiteshttp//en.wikipedia.org/wiki/Airbus_A320_familyhttp//www.airbus.com/aircraftfamilies/passengeraircraft/a320family/a320/http//www.flightglobal.com/directory/BooksMass Balance and Performance by Jeppesen GmbH, Frankfurt, Germany 2001