Modern Trends in Aircraft Electrical System (Essay Sample)

Modern Trends in Aircraft Electrical System Name: Institution: Modern trends in aircraft: Aircraft Electrical System Introduction The aircraft industry is adapting to all electric and more electric system (MEA) to cater for the increasing demand for electric power in the aircraft Agarwal (2012). The trend of all electric and more electric aircraft is aimed at replacing the traditional hydraulic and pneumatic systems, which had limited monitoring features, compromised comfort, reliability and safety. MEA structural design is intended to improve maintainability, reliability, flight safety and efficiency in the aircraft industry Agarwal (2012). Moreover, application of MEA reduces the emission of air pollutant gases from the aircraft significantly, which greatly contribute in solving some of challenges of climate change. Aircraft industry has experience-increased usage; thus, it must not only meet the expectation of the customers and comfort but must also abide by the existing laws and regulation such as environmental pollution laws. Such goals and objectives cannot be achieved using the traditional aircraft system. The industry further has the responsibility of taking the advantage of the emerging technologies and embracing them to improve efficiency, effectiveness and reliability (Abdel-Fadil el al, 2013). More electric aircraft (MEA) concept Both the civil and the military aviation industries are witnessing tremendous progress and rapid transformational change, for example, currently commercial aircraft has the capability to operate at weights of over 300, 00kg and can fly up to 1600km in nonstop journey at amazing speed of 1000km/h (Agarwal, 2012). The conventional aircraft uses a non- propulsive system. The system is driven by amalgamating different secondary power drives or subsystems such as hydraulic, pneumatic, electrical and mechanical systems. These power drives depend on a sole source, which is the aircraft main engine. Power subsystems are run using different methods, unique to each subsystem. For example, extraction of mechanical power from the main engine is by a driven shaft, which transmit the power to the gearbox to drive lubrication pumps, fuel pumps, hydraulic pumps and electrical generators. Pneumatic power is obtained by bleeding the compressor which intern drives turbine motors in the engine’s starter subsystem, the wing anti-icing system and environmental control subsystems. The electrical power and hydraulic power secondary drivers are circulated through the aircraft for driving actuation system such as flight control actuators, landing gear brake, utility actuators, avionics, lighting, galleys, commercial loads and weapon system (Agarwal, 2012). The combination nature of the conventional system makes it complicated and bulky. This reduces the efficiency of the aircraft functioning. For instance, if the pneumatic or hydraulic system experiences leakages, the aircraft would be grounded for a long period; this may lead to inconveniences to users of airplane transport system especially the business people and the transportation of perishable goods (Abdel-Fadil el al, 2013). Locating the leakage is a daunting task that consumes both time and resources, this may lead to losses on the side of the aircraft owner due to lost working days and the expenses incurred in terms of compensation and repair. It is in this regard that the industry is moving away from the conventional system, towards more efficient electric system. The recent technology in power electronic system, fault tolerant electric machines, electro hydrostatic actuators and electromechanical actuators, has immensely boosted the concept. The concept has been applied in different systems in the aircraft such as, engine system, hydraulic system, electrical system, engine and APU start, environmental control system, wing protection system, and APU system. The Subsequent paragraphs discuss the application of MEA in these systems and their benefits (Abdel-Fadil el al, 2013). Engine system Secondary airplane system power needs in the conventional system is sourced from the engine in pneumatic form, this requires more horsepower, which leads to more fuel consumption, and the engine that supports the pneumatic system is complicated and heavy Sannet (2007). MEA solves this problem by introduction of electrical form power system, which is drawn from the engine by use of shaft driven generators. This means that pneumatic subsystem has been rendered redundant, the electric form supports more efficient engine operation because the overall level power requirement is reduced, the electric form requires less power compared to the pneumatic form. Electric form uses reduced horsepower resulting to reduced fuel consumption. An engine that uses electronic power system does not need pre-coolers, control valves or pneumatic ducting; these engines are simple in nature and have reduced weight (Sannet, 2007). Hydraulic system Conventional centre hydraulic system is powered by two air-turbines driven by a hydraulic pump, the turbine powers the system during the landing and takeoffs, the remainder part of the journey is powered by two small electric driven pumps. The combination of the air turbines and the small electronic pumps makes the system bulky and heavy. This challenge is solved by use of electronic motor to drive the pumps instead of the air turbines; this makes the system smaller and more efficient (Sannet, 2007). Electrical system The electrical system in MEA is a hybrid voltage system, which is greatly expanded. It can generate twice as much electricity as a conventional electric system. The arrangement of the generators, two per engine and two per APU, significantly reduces the generators’ feeder weight. The generators lack the complex constant speed drive thus are more reliable, require less maintenance and have lower space cost (Sannet, 2007). Environmental control system More electric aircrafts use adjustable electrical motors; this optimizes the airplane energy usage, because, there is no need to supply the excess energy from the compressed air. This means that the energy is not lost, improving the engine fuel consumption. System air inflow is adjustable depending on the number of the aircraft occupants to limit energy wastage (Sannet, 2007). Wing ice protection system In the conventional system, airplane bleed system supplies hot bleed air to the areas of the airplane wing that needs protection from the ice. The system uses more power because there is lose of excess energy through exhaustion. Modern wing protection system uses electro thermodynamic ice protection scheme Sannet (2007). The system uses heating blankets in transmission of energy to the areas of the wing that require protection. The system is more efficient when compared to the conventional system because there is no energy los...