Aero Power
emerging technologies in electrical drives and power distribution systems in future aircraft
The new technologies in electrical drives and power distribution systems in future aircraft
u.sureshkumar *
* Professor in the Department of Electrical and Electronic Equipment
University Mohamed sathak Advisor
Kilakkarai
E-mail: uskrk@sify.com
Abstract:
It is expected that in future aircraft, all powers, except for propulsion, will be distributed and handled electronically. In other words, the power will be used to fly aircraft subsystems currently powered by hydraulic, pneumatic or mechanical including utilities and implementation of flight control system of environmental control, and lubrication pumps fuel, and many other utility functions. These concepts are embraced by what is known as the "More Electric Aircraft (MEA)" initiative. The MEA focuses on the use of electric power instead of hydraulic, pneumatic, mechanical and energy to optimize performance of the aircraft and the cost of the life cycle. It would eliminate the need for gearboxes and emissions of the power transmission is by mechanical means instead of reducing the weight of the aircraft and fuel consumption increases. A detailed analysis
interaction between an actuator electro-mechanical systems (AMS) system connected to the DC bus power distribution in an aircraft the next generation of bus controller transport is presented. Development of electrical control systems Trust-by-wire for aerospace applications recently requested to remove the aircraft hydraulic systems. Plan
Engineers have tested electrohydrostatic actuators (EHA), which combined electricity and hydraulics, hence
evolutionary "more electric aircraft" idea. Efforts are underway replacing
hydraulic systems with electrical systems, leading to a new technology called "All Electric Aircraft.
Introduction:
Flight Control System
A flight control system consists control surfaces, flight control of the respective cockpit, the linking mechanism and operational requirements for aircraft in flight cont4rol.
Classification
flight control system (FCS) are classified as follows:
- Mechanics FCS
- FCS Hydro Mechanical (Voltage control units of flight (PFCU))
- FCS Fly-by-wire
FCS mechanical
The FCS mechanical models are the most basic. It is used in aircraft at the beginning and now small planes, where the aerodynamic forces are not excessive. The FCS uses a collection of mechanical parts such as rods, cables, pulleys and sometimes chains to transmit the forces of the interior controls to control surfaces.
Hydro Mechanical FCS (voltage control units flight (PFCU)):
Complexity and the weight of a mechanism significantly increases the size of the FCS and the aircraft performance. Hydraulic Power overcomes these limitations
A FCS Water has two parts:
- Circuit mechanical
- The hydraulic
The circuit links the mechanical position steering with hydraulic controls. As the FCS mechanics, it has a straw, chains, cables, pulleys, and sometimes. The hydraulic pump hydraulic piping, valves and actuators. The hydraulic pressure generated by pumps in the power of the hydraulic jacks. Actuators convert hydraulic pressure in the movements of the control surface. The servo motion actuators. The system of control over them has a drawback that contains heavy mechanical circuits, which increases the weight of the system. To overcome this problem a new technology "more power evolution of aircraft" has been developed. The plane in which this technology has been used called "more electric aircraft (MEA).
In describing the MEA, the flight control systems of control can be considered as participation two major technology areas: "fly-by-wire (FBW) and power-by-wire (PBW). FBW technology includes the design, development and implementation of e-commerce systems for control Vol. The electronic control controls the functionality of flight control and actuator implemented using centralized or distributed architectures. distributed control systems to reduce the processing load of centralized control equipment theft and provide more flexibility in architecture Development System. Another advantage is the weight reduction achieved by reducing the beam size and the number of components. In recent years, Technological advances have focused on FBW field, since the FBW control systems are now the norm in commercial and military aircraft today. Power-by-wire (PBW) player is the next step in the control of the aircraft. In the same way and a flight control system eliminated the need for wire connections for mechanical actuators, power-by-wire eliminates the need for hydraulic systems. controlling power comes directly from the device's circuit. This has several advantages. hydraulic power station are complex and difficult to maintain. The elimination of these systems significantly reduce the amount of support equipment and personnel necessary to operate and maintain air flow and space vehicles. In addition, PBW actuators have the potential to be more efficient than their hydraulic counterparts. A hydraulic system must generate and maintain significant hydraulic pressure (3000-6000 psi) at any time, regardless of the application. PBW actuators use power only when necessary. Finally, drive systems PBW can be much more fault tolerant than those who rely on a central hydraulic supply. Once hydraulic line is compromised, usually leads the loss of all hydraulic system. Consequently, several hydraulic circuits are required to maintain a certain level of redundancy. With a set of PBW, a actuator can not simply be turned off, isolate the problem to a single surface.
PBW type actuators
There are several types of PBW actuators, including actuators electrohydrostatic (EHA) and electromechanical actuators (EMA). Pumpmotor EHA using a Reversible fluid pump, electrically driven hydraulic self directly to a piston. This leads to the RAM in the same manner as standard hydraulic cylinder (Figure 1 (a)). EMA does not have an internal hydraulic fluid instead of using electric motors directly through RAM a manual gearbox (Figure 1 (b)). Compared to an EHA, the EMA has certain advantages. It is lighter, smaller and less complex an equivalent EHA because of the lack of internal hydraulic system. Since there is no hydraulic fluid in the load path, EMA tends to be more rigid than an equivalent EHA. The EMA tends to be more efficient because there is no drift or loss of pump inefficiency. Finally since there is no possibility of discharge with the EMA, which is better suited to long-term storage or space applications.
Driving Electromechanical (EMA)
A mechanical device EMA uses an electric motor coupled to a surface flight control. This is achieved using a box of engine speeds, and depending on the mode of operation is necessary, may include some type rotary to linear conversion, as a ball screw. The electric motors that require a DC power supply normally used, but the addition a diode rectification stage also authorized to operate an AC source. Engine speed, direction, and they translate directly to speed, direction and load on the cylinder. Figure 1 shows an EMA is being developed by TRW for an application to flight control levels. In its basic form, the college is subject to certain shortcomings one point that may lead to a mechanical blockage, and therefore have difficulties certification flight to certain areas. Additional devices can be used to alleviate this problem, but in doing so, the complexity, cost and weight. For these reasons, the EMA-based applications is not appropriate for primary flight control. However, systems and subsystems spoiler actuation EMA technology can accommodate.
system evacuation EMA
Great flight controls for high power EMA
Power Architecture Based System
The proposed electricity distribution system is based on a 270V DC distribution bus. The typical power system architecture reference in a new-generation aircraft is shown in Fig. 1. We can see that the basic elements that control of power converters are bidirectional power (BDC). A bus controller provides an interface between the starter / generator and the distribution bus. Most loads, including actuators, are governed by power converters bi-directional, which control the power and status of the DC bus.
With the proliferation of power converters and bidirectional actuators in the distribution system peak power is important to develop methods for analyzing the interaction between different subsystems. Because of the complexity of power system reference the large number of subsystems, a spectacle of a power distribution system, which captures the essential characteristics of the reference system, but it is not so complicated, is introduced. The electrical system of the sample is represented as an interconnection of a source and under-charging system.
Example System Power Distribution
The Example of electricity distribution network in Fig. 2. The source of the subsystem represented by a sub-system consists of a source ideal three-phase rectifier voltage pulses in three phases to facilitate the regulation required by DC 270V DC bus. The burden represented by the subsystem subsystem 2 is an electromechanical actuator used for control surfaces Flight control on the side. Other charges on DC bus are modeled by a current source or a simple resistance.
The EMA model is shown in Fig. Figure 5 shows to include a DC motor with constant field, a ball screw transmission between engine and control surface, and a dynamic model of the surface. The motor voltage is controlled by a PWM Buck Converter with bidirectional input filter. EMA is controlled by a multi-loop controller, which includes a DC motor, motor speed and spindle load position loops.All comments buses are modeled by a resistor or a source of supply.
Electro hydrostatic actuator (EHA)
- In contrast to EMA, EHA (Figure 2) fluids used gear between the electric motor and the disc surface. provides a means of hydraulic oil through the transmission of power surface. Here, a variable speed electric motor (usually CD) is used to drive a fixed displacement hydraulic pump, which feeds its turn a conventional hydraulic cylinder piston. Change of direction is achieved using a bi-directional motor. A major advantage of this approach is that the EHA mode does can be given as a conventional hydraulic cylinder. This approach is performed using the standard bypass or valve hydraulic damping (Figure 3), the traditional assets of waiting, or active-active configurations of actuators can be easily adopted. This capability allows applications most appropriate for EHA flight control primary EMA. Although the hydraulic technology restores the EHA and liquid components, is completely independent within the actuator assembly. Compared to traditional hydraulic systems, the inconvenience of disconnecting the water supply Fuel and bleeding complications during the relocation is not the system during maintenance.
electrohydrostatic actuators (EHA)
Great EHA
Control Regime EHA
Advantages of electric actuators:
Advantages action potential Electrical system level have been published.
electric drive can provide:
- Improved maintenance On aircraft:
- Less than hydraulic components are necessary,
- Faster delivery of aircraft,
- Fewer parts parts and tools are needed
- Improved fault diagnosis via high-test (BIT).
- Improved availability system reliability:
- electricity distribution is more practical and offers the flexibility of the system compared to a capability reconfiguration former Ñ difficult to achieve using hydraulic
- Improving mean time between failure (plasma) by eliminating (EMA electromechanical drive) or use the application (or reader electrohydrostatic EHA) of hydraulic components.
- Improve Flight Safety in N MEA configuration, enhanced security system is provided by various sources of power to the actuator and prevention of common mode failures.
- savings system weight reduction weight n, obtained by replacing all the hydraulic systems, including pumps, distribution systems (pipelines and liquid), and valves, electrical systems.
The main advantage is the reduction of aircraft costs, for example, reduced fuel costs (due to weight reduction), and low maintenance costs (Quick). However, before these benefits can be achieved, additional work is needed to improve technology and provide of application platforms appropriate to introduce the technology in use.
In addition, the aircraft maintenance industry needs to align its infrastructure so you can enjoy the benefits of electric technologies.
Some additional advantages of both EMA and EHA actuators are following:
- Under the energy consumption during idle operation waiting
- The rapid implementation of response
- It can be easily adapted for use with AC or DC
- Insensitive to changes in the frequency of AC service Electric.
EHA versus EMA?
An alternative to the EHA are "actuators Electromechanical (EMA), in which torque is mechanically amplified and transmitted to the control surface with a set of gears, screws or any other mechanical transmission device, can be considered as an alternative. In fact, as far as the complexity of weight, reliability and concerns maintenance, EMA is potentially more attractive than EHA, at least for low-power applications. In particular, every water technology issues relevant are obviously removed from the configuration of the EHA. However, in the following three areas are preferable to EHA EMA:
? The interference probability of EMA used in an application of primary flight control is difficult to predict and justify the basis of experience in the service. the likelihood of interference from EHA, can be evaluated directly from the experience of the current servo control, and indicated that "very unlikely, but ignored. In contrast, the probability of mechanical locking systems incorporating hundreds of teeth of gears and mechanisms screw is questionable and being acquired in the application of secondary flight control can be transferred directly to the primary flight controls because of very different work cycles, in particular,
Wear parts and components can cause a control surface mechanical "Free play" or other non-linearities, which can lead to an unacceptable limit cycles
? EHA The introduction of a servo in parallel with the regular basic architecture described above "more electric" is easier for a BMA. EHA can be easily reversible mode, may include damping devices identical to those currently used for the protection of beats, and can be constructed many common elements with the adjacent servo, such as the piston, cylinder, or position sensor coupled to the accumulator. In an obvious choice to disseminate technical and financial risks, Airbus has asked the talents of several companies to design, production and supply of most actuators jumbo jet. In particular, the A380 and EHA lift of the wing and rudder EBHAs purchased from Goodrich, Messier-Bugatti will supply the corresponding EHA bombs. During This time, the spoiler is EBHAs Liebherr, which provides its own bombs. Phil Hudson, vice president of engineering for the systems Goodrich Drive notes: "The concept Electronics EHA can also be designed to serve more functions than motor control, simply. It can serve as the controller actuator Intelligent right and as part of a distributed control system or control of a set of several actuators. Another advantage is that distributed intelligence technology enables local performance elements in a system of control and can significantly reduce weight and improve troubleshooting harness and isolation. "
Maintenance services are also important. Power-by-wire "units of action EHA-extractable are online with only mechanical and electrical connections plane, which eliminates the need to fill or purge the hydraulic system fluid is necessary for the central hydraulic system. Since electric actuators-by-wire "are independent and located at a distance the surface, the surface damage is significantly reduced. In addition, the power wire actuators can be designed to be sensitive to the position, which means that the actuators that provide the flow and pressure needed to move and maintain the actuator in a desired
position. The conventional hydraulic systems are configured to produce a continuous pressure. The flow is measured at each actuator, which can lead to high energy and generate unwanted heat. William Schley, R & D, Parker Aerospace, Control Systems Division, explains that only EHA energy demand. In particular, consume energy in proportion to the power delivered to the load. In contrast, a conventional servo drive equipped with hydraulic EVSV consumes power in proportion to the output speed, the load balancing power output if needed, with the rest of the power dissipated by the pressure drop (heat) through the main control valve. Although hydraulic actuators to be more efficient, you load, the loads are generally low for most of the flight. "Another important benefit of electric actuators is survival. Ballistics or explosives to harm a system of electricity distribution or actuator does not usually cause loss of function of the entire carcass, especially if the damage is peripheral. In a hydraulic system, according to its design, even a small leak can cause a significant loss of function and / or fire. Although some contain electric actuators
hydraulic fluid, the system as a whole is still usually more than survival. For the moment, these advanced features of management failure are provided by the EHA and its variants. EHA blends classical and best electric drive system hydraulic hybrid design approach, which is more tolerant of failures the most common EMA. In addition, EHA is mechanically simple, and free jam gear train. The storage capacity of typical long-term EHA is 10 years or older.
Next generation all-Electric Aircraft —:
The all-electric "Aircraft is a concept that has emerged in the 1970s and has generated much research. An all-electric engine that could replace current aero gas turbines, all lead electric, through a distribution network, the coils of the motor / generator integrated into engine. The extent of motor and generator to include services such as active magnetic bearings facilitate removal of oil system. The all-electric concept of offering a vast field for both engine and the reconfiguration of the cell and operational improvements, with studies indicating the benefits of reduced total weight, greater reliability, easier maintenance, reduced operating costs (including consumption of reduced fuel), and greater security.
Conclusion
From the hypothesis of a single hydraulic power replaced by an electric, it is possible to establish the relativity and the magnitude changes required in migrating to the concept of "all-electric aircraft". In a small civilian aircraft, usually a minimum of five electric actuators would be required to provide pathways for electrical control surfaces of primary flight control. If all the hydraulic systems have been converted to electricity, more than 20 electric actuators would be needed to ensure complete control of all primary and secondary flight control surfaces. Increasing of electricity demand has significant implications for electricity generation and distribution. Therefore, a significant amount Work still needed to deal with the consequences of distributing many electrical drives around an airplane, and after startup, steady state and peak demand for deliveries of fuel necessary for electricity.
It is clear that migration electric drive systems affecting the civil and military markets. As described above, the substitution of a hydraulic system single replacement feeding is an important step in the transition to all-electric technology. It is clear that the requests are made of generators the plane and distribution architectures will increase significantly to meet the needs of this migration. A company called TRW has already developed products to meet the current requirements of PBW and offers programs to ensure they comply with all requests required by future all-electric aircraft. Finally, it is expected that, once in service, technology, electrical controls and architectures electrical system will increase the commercial viability and reliability of service cells to which they are installed. These improvements will undoubtedly promote the adoption of higher levels of electrical activity of future aircraft.
References:
- J. Weimer A power management "and distribution, with more electric aircraft", Proceedings of the30thIntersocietyEnergyConversion Engineering Conference, vol. 1 July 1995, pp. 273-277
- Technology Review Journal – Fall • Millennium Edit / Winter 2000
- Overview Development OPERATOR
D. Tesar, UT Austin, April Robotics Research Group 1, 2006
About the Author
What can I do with a degree in aerospace engineering?
I'm so in love with the aircraft, brute force at their disposal and elegance flight. But I've been watching some of the job for an engineer of Aero and most of these jobs were "avionics, thermal dynamics, fluid dynamics, etc. … "And all these jobs for an EA does not seem to affect the location of the plane that interests me Should I stay with AE or ME may be one and the work of mechanics from the plane? (I'm not really sure that the work of engineers whose components if) Thanks!
Fluid Mechanics and Thermodynamics are part of aerospace engineering, combined to form aircraft. And engineers can work on the aircraft structure and mechanical structures.
Hydro Aero Power
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