We Have Numbers Of Free Samples

Introduction

This paper will describe the basic operations of a hydraulic system along with the operations of cabin ECS of an aircraft. Moreover, the operations as well as layout of the protection system of an aircraft will be described in this project. Apart from this, the operations of fuel systems are described in this paper.

Task 1: Explore the Design and Operation of a Basic Hydraulic System

1. The system requirements, fluid properties, design and operation of aircraft hydraulic power supply systems.

Hydraulic system generally uses a fluid under pressure for driving the machines or moving some mechanical parts.

The system requirements of the aircrafts systems of the hydraulic power systems will include the following:

• Prime mover that will be the outside power source for driving the hydraulic pump
• Hydraulic pump based on Variable- displacement
• Hydraulic motor

Hydraulic systems will have the hydraulic fluid along with three other mechanical parts, which are “pressure generator”, “motor” that gives the power and “plumbing” that supplies the fluid inside the aircraft as per the requirement (Mangione et al., 2016).

By the use of fluids, hydraulic systems supply the energy and for the theoretical as well as practical purposes, any fluid can be used. The fluids must have the following properties:

• Flash point should be high
• Adequate viscosity
• Properties of a lubricant
• Conductivity

Figure 1: Hydraulic power pack

The system of hydraulic power supply is the small unit that includes the electric pump, reservoir, PRV or pressure relief valve, filters as well as valves (Fielding, 2017). With the implementation of this system, there is no need of a centralized system for hydraulic power supply along with the long lines of the hydraulic systems that helps to reduce the weight of the system. They can be operated by the engine gearbox or by the electric motor. These systems help in controlling the landing gear, FCS and stabilizer trim that eliminates the use of the centralized system.

2. The design and the operation of aircraft landing gear and hydraulically powered flying control systems and the function of their components.

The landing gear of an aircraft generally supports the total weight of aircraft while landing as well as ground operations. The landing gear is fitted to the aircraft in the primary structures (Mueller and Oswald, 2017). Different types of landing gears are used for different operations such as fixed, retraction type, shock absorbing landing gear and the non-shock absorbing landing gear.

Figure 2: Landing gear
(Source: Created by learner)

Design and the Operation:

The landing gear will consists of the upper link and lower link that are hinges to the centre, which allows the brace to control in the gear retraction of the aircraft. Moreover, the upper end is attached to the axis within the wheel and in the shock strut, lower end remains attached. A locking link is included in between shock strut and drag link. The lock link is adjusted with the down piston for holding the brace links of the sides in the central position (Wong et al., 2018).

Hydraulically powered flying control systems are included in the high-speed aircrafts that have supersonic speeds. They will have high air loads and manually controlling of the aircraft is not possible. In the hydraulically powered control systems, a hydraulic actuating cylinder is used for controlling the linkage for helping the pilot in order to move control surface. Hydraulic actuator or PCC that is installed in the control linkage controls each of the movable surfaces.

3. The design and operation of hydraulic, power supply, landing gear and flying control systems and their components.

Apart from the design and functionality, the hydraulic systems have some of the basic components that allow the fluid to transmit. The components include the following:

• Pump
• Check valve
• Reservoir directional valve
• Actuator
• Pressure relieve valve
• Fitter

The power supply of the aircraft includes the following components:

• Generators (DC and AC)
• Buses
• Transformer Rectifier Units
• Motor Drives
• Motor controllers
• Contractors
• External power
• Batteries
• Loads and
• Sensors

Landing gear of the aircraft consists of the following components:

• Torque links
• Hydraulic gear retraction system
• Trunion as well as bracket arrangements
• Sensors
• Lockers
• Strut linkages
• Indicators

Components of the flying control systems are as follows:

• Auxiliary servo cylinder
• Primary servo cylinder
• Mixing units
• Swashplate

4. The operation of hydraulic, landing gear and flying control systems and their components contribute to safe flight.

The hydraulic system helps in enhancing the ease along with the accuracy to control the aircraft. Moreover, the force gets multiplied by the implementation of the hydraulic system and will maintain the constant force as well as torque regardless of the variations in the aircraft speed. Apart from this, the hydraulic systems are simple as well as safe for the flight. The landing gear helps in the distribution of the weight of the aircraft at the time of landing. More the wheels on the middle of the aircraft more will be the balance, as they will hit the ground first and the majority of the force will be experienced in the middle. Moreover, the front landing gear helps to increase the balance (Hu et al., 2015). However, the components of the landing gear works uniformly to maintain a safe flight.

With the implementation of the control systems in the flight, there will be less maintenance as the wires will have less weight. It will add precision to the surface movement as well as enhance interface, which is also a great contribution for a safe flight (Szafir et al., 2017).

Task 2: Design and Operation of Cabin Environmental Control Systems

1. Pneumatic system requirements and the control and distribution of air supplies to the aircraft services.

The pneumatic system uses the compressed air that will act as the working fluid alike the hydraulic systems. In comparison to the hydraulic, pneumatic systems will use air for transmitting the power inside the aircraft. The requirements of the pneumatic system will be backup systems, Low-pressure systems as well as high-pressure systems.

The main requirements of the pneumatic systems will include the following:

• Intake filter
• Compressor
• Cooler
• Separator
• Receiver
• Secondary air treatment
• Control wave
• Actuator
• Motor control centre and
• A pressure switch

2. The design and the operation of oxygen, pneumatic air supply, air-conditioning and pressurization systems and the function of their components under normal and emergency operating conditions.

Inbuilt oxygen systems in the aircraft are used in the passenger aircrafts in which gaseous oxygen or oxygen generators are used as per the requirement. The gaseous oxygen systems consist of the portable cylinders along a single mask via a hose. The regulators are used for dispensing the oxygen along with a continuous flow of oxygen allows the oxygen to exit from the storage tank with the help of a valve and pass through the reducer.

The pneumatic air supply uses the compressed air as the fluid for acting like the hydraulic systems. Some aircrafts will include the airstart system in which pressurized air within the bottle will help to start the engine (Hoffjann et al., 2019).

The air conditioning systems of an aircraft are of two types that commonly used. “Air Cycle Air Conditioning” is used in the aircrafts that are powered by turbine. In the reciprocating aircraft, the vapor cycle system is used.

Figure 3: Air conditioning system of Boeing 737

The pressurization system ensures the safety as well as comfort of all the individuals present in the aircraft by controlling pressure of the cabin and the exchange of inside and outside air.

3. The design and the operation of the aircraft environmental control systems and components under normal and emergency operating conditions, assessing the contribution made by each system to the safety of the airframe and personnel.

Figure 4: Environmental control system of an aircraft

The aircraft ECS helps to regulate the pressure, humidity, temperature as well as ozone for maintaining the safety and comfort of the cabin. ACM will provide the cooling along with dehumidification for removing the heat of bleed air from the engine (Heuer et al., 2019).

The following systems are responsible for the safety of all the passengers and crews within the aircraft:

• BFS or Bypass flow subsystem
• Controller
• Catalytic Converter
• Outflow systems
• Engine bleed Air
• Trim air flow system
• Thermal & moisture loads systems

Task 3: Operation and Layout of Aircraft Protection Systems

1. The layout and operation of aircraft ice protection systems as well as function of system components, under the normal and emergency operating conditions.

Generally, there are two designs for the aircraft ice protection system and they used for removing the ice after formation or for the prevention of ice formation. The first system is known as “de-icing system” and the other one “anti-icing system”. These systems works in that weather condition where there is a risk of ice formation.

Figure 5: Aircraft ice protection system

2. The layout and operation of aircraft fire detection and extinguishing systems and associated components under normal and emergency operating conditions.

The fire detection system helps in sensing the presence of fire or overheating inside the aircraft. These units are installed in various locations, where there is a risk of fire. Three major components of the detector system are “thermal switch”, “Thermocouple” and “Continuous-loop” systems. Along with these, the different compartments of the power plant are divided in zones depending upon the airflow (Blanchard and Bryant, 2015).

3. The layout and operation of ice protection and fire detection and extinguishing systems and associated components under normal and emergency operating conditions.

Engine fire protection system will include overheat as well as fire detection system that are controlled by battery bus and fire extinguishing are controlled by hot battery bus. Each of the engines has eight detectors for monitoring the four areas of engine. However, the de-icing system have two different attributes, those are implementing different ways in transferring the energy that is used in ice removal (Chasen et al., 2017). The second attribute comprises of the efficiency of energy that is used in removing ice periodically.

4. Analysis of the layout and operations of ice protection as well as fire detection and extinguishing.

As compressor bleed air is used for the ice protection, they will never run out in the service. Moreover, in case of weeping wings, the TKS fluid that makes a layer to protect will protect the total airfoil surface. The bleed air from the running engine can prevent formation of the ice. However, the fire detection as well as extinguishing system within an aircraft allows the detection as well as protection from the various fire risks in the some specific areas along with the entire cabin (Heuer et al., 2019).

Task 4: Layout and Operation of Airframe Fuel System

1. The layout and operation of a typical airframe fuel system

The aircraft fuel system helps in enabling the fuel for loading, storing, managing as well as distribution to the engines efficiently. These systems will be different in different aircrafts in terms of their size and complexity. In general, the fuel system of an aircraft will have a single fuel tank that will be gravity feed along with the fuel lines to engines.

2. Properties, use and safe handling of the different aircraft fuels and the nature and function of airframe fuel system components.

Aircraft fuels are made of various hydrocarbons that are refined by the fractional distillation of the crude oil as per their boiling points. The different properties of the aircraft fuels are as follows:

• Hydrocarbons ranging from C4 to C10
• Volatility
• Less impurities
• Using fuel filters that prevents fuel microbes
• Higher octane number
• Flammability property of the fuel

3. Layout and the operations of airframe fuel system and their components for all the operating modes

The various operations of the components of the aircraft fuel systems are discussed below:

• Fuel tanks: They are used for loading, storing, managing as well as distribution of fuels to the engines efficiently.
• Fuel linings: They are flexible as well as rigid depending upon the application as well as location (Wong et al., 2018).
• Fuel valves: These valves are used for shutting off the flow of fuel and routing the fuel in the required location. Along with it, the fuel pumps, fuel filters, fuel heaters as well as fuel system indicators are also there for the effective functioning of the aircraft fuel system.

4. Analysis of the layout and the operation of airframe fuel systems

The benefit of the aircraft fuel systems is to reduce the cost as the components include simple components as they very easy to manufacture. Secondly, the components of the fuel systems are very reliable and accuracy of the operation is high.

Conclusion

In this report, the first section includes the description of the design and operation for a hydraulic system followed by the description of the operations of cabin ECS or environmental control systems. Moreover, the operation as well as layout of APS system has been carried out. Finally, this report describes the operations of aircraft fuel system.

[Download not found]

Download