Integrated Aircraft Electrical Power System Modeling and Simulation Analysis PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Integrated Aircraft Electrical Power System Modeling and Simulation Analysis PDF full book. Access full book title Integrated Aircraft Electrical Power System Modeling and Simulation Analysis by Jon Zumberge. Download full books in PDF and EPUB format.
Author: Jon Zumberge
Publisher:
ISBN:
Category :
Languages : en
Pages :
Get Book Here
Book Description
Author: Jon Zumberge
Publisher:
ISBN:
Category :
Languages : en
Pages :
Get Book Here
Book Description
Author: AE-7M Aerospace Model Based Engineering
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
Get Book Here
Book Description
The objective of this document is to define basic terms and definitions and to provide general guidance for M&S of aircraft EPS. This document establishes basic terms and definitions applicable for modeling and simulation of aircraft electric power systems. It lays the foundation for a series of AIRs and ARPs within the scope of the SAE AE-7M committee.
Author: Susan Hanke
Publisher:
ISBN:
Category :
Languages : en
Pages : 153
Get Book Here
Book Description
A modeling and simulation based methodology is proposed that introduces the new capability to conduct rapidly consistent and integrated power system architecture trade-off studies at aircraft level in the preliminary design phase of civil aircraft. Conventional and new architectures (e.g. more electric, bleed-less) can be built and analyzed rapidly, sensitivity studies are enabled. A methodology based on the formalization of a parametric power system architecture sizing process combined with a performance analysis process is developed. Dedicated function-based models integrating the operational space (time dependence, failure and degraded modes) are proposed and a modular structure enabling a multi-level modeling approach is elaborated. Three applications illustrate the new capabilities introduced by the developed simulation framework prototype: the aircraft level comparison of different architectures, the electric generator sizing synthesis and the link of power systems simulation to an aircraft global thermal model.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages :
Get Book Here
Book Description
Author: David Andrew Woodburn
Publisher:
ISBN:
Category :
Languages : en
Pages : 163
Get Book Here
Book Description
Modern aircraft, military and commercial, rely extensively on hydraulic systems. However, there is great interest in the avionics community to replace hydraulic systems with electric systems. There are physical challenges to replacing hydraulic actuators with electromechanical actuators (EMAs), especially for flight control surface actuation. These include dynamic heat generation and power management. Simulation is seen as a powerful tool in making the transition to all-electric aircraft by predicting the dynamic heat generated and the power flow in the EMA. Chapter 2 of this dissertation describes the nonlinear, lumped-element, integrated modeling of a permanent magnet (PM) motor used in an EMA. This model is capable of representing transient dynamics of an EMA, mechanically, electrically, and thermally. Inductance is a primary parameter that links the electrical and mechanical domains and, therefore, is of critical importance to the modeling of the whole EMA. In the dynamic mode of operation of an EMA, the inductances are quite nonlinear. Chapter 3 details the careful analysis of the inductances from finite element software and the mathematical modeling of these inductances for use in the overall EMA model. Chapter 4 covers the design and verification of a nonlinear, transient simulation model of a two-step synchronous generator with three-phase rectifiers. Simulation results are shown.
Author: Mark Ahlers
Publisher: SAE International
ISBN: 0768083044
Category : Technology & Engineering
Languages : en
Pages : 117
Get Book Here
Book Description
The simultaneous operation of all systems generating, moving, or removing heat on an aircraft is simulated using integrated analysis which is called Integrated Energy System Analysis (IESA) for this book. Its purpose is to understand, optimize, and validate more efficient system architectures for removing or harvesting the increasing amounts of waste heat generated in commercial and military aircraft. In the commercial aircraft industry IESA is driven by the desire to minimize airplane operating costs associated with increased system weight, power consumption, drag, and lost revenue as cargo space is devoted to expanded cooling systems. In military aircraft thermal IESA is also considered to be a key enabler for the successful implementation of the next generation jet fighter weapons systems and countermeasures. This book contains a selection of papers relevant to aircraft thermal management IESA published by SAE International. They cover both recently developed government and industry- funded thermal management IESA such as the Integrated Vehicle Energy Technology (INVENT) program, and older published papers still relevant today which address modeling approaches.
Author: Adam B. Donovan
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 72
Get Book Here
Book Description
Many advances in technology are expected to increase the capabilities of next generation aircraft, and these advances will increase the thermal load on the aircraft as well. In order to assess and account for these increased thermal loads, three studies were performed: a fuel pump trade study, a high energy pulsed system (HEPS) implementation study, and a legacy vehicle environmental control system (ECS) study. The fuel pump study addresses the effect of the implementation of a centrifugal fuel pump versus a variable displacement fuel pump. Traditionally, aircraft designers have used a centrifugal fuel pump over a piston based pump based primarily on mass, volume, cost, and reliability. This study considers specific excess power (SEP), fuel burn and thermal margin and shows the piston based pump performing superior mainly because it eliminates fuel recirculation resulting in an increased thermal margin. This investigation demonstrates the benefit of capturing component level models and thermal concerns in the conceptual design process. Both of these issues are vital to the development of future aircraft designs. Additional research needs to be completed to compare both pumps based on the mass and volume of each system. The second study investigates the implementation of a HEPS device at an air vehicle level. HEPS generate excessive amounts of heat during operation, creating challenges in how to integrate them into an aircraft without overwhelming the vehicle’s power and thermal management systems (TMS). In order to evaluate the impact of the HEPS electrical and thermal load on the aircraft's mission, a vehicle level modeling and simulation (M&S) effort must be executed of the power and thermal management systems. To accurately evaluate the total effect on the aircraft, the HEPS must be integrated into a Tip to Tail (T2T) model of the system that includes the aircraft power and thermal management subsystems. With the HEPS system integrated into the T2T model, not only can its mass and volume effects be analyzed, but also the transient power and thermal loads created by the new system can be evaluated for their effect on other aircraft subsystems. Furthermore, the aircraft subsystems can be optimized to vehicle level metrics instead of subsystem level only. This will result in a more effective and balanced overall aircraft design. Using a T2T model to evaluate the integration of a HEPS system on an aircraft will enable assessment of its overall impact to next generation aircraft. Therefore, the significant impact of highly dynamic power and thermal loads on next generation aircraft is addressed. The third study is the implementation of an air cycle based ECS in a legacy (4th generation) air vehicle. Relatively few attempts have been made to define appropriate validation testing constructs for T2T analysis in a transient mode of operation. Current research addresses the process of validation testing using legacy aircraft systems in order to acquire relevant data that will lead to the validation of existing models, and different modeling methods. The model developed in this work will eventually be utilized in these validation efforts at a later date. To this end, an air vehicle system (AVS), turbine engine, generator, and environmental control system (ECS) have been modeled in a T2T model of the actual legacy system. In particular, this study will focus on the creation and integration of the ECS model. The ECS uses an air cycle machine, which utilizes a Brayton refrigeration cycle to cool the air to the cockpit and avionics. The ECS model will be shown to successfully cool these components while subjected to varying bleed rates from the turbine engine.
Author: Jenica-Ileana Corcau
Publisher:
ISBN:
Category : Electronic books
Languages : en
Pages : 0
Get Book Here
Book Description
The current challenge in aviation is to reduce the impact on the environment by reducing fuel consumption and emissions, especially NOX. An open research direction to achieve these desideratums is the realization of new electric power sources based on nonpolluting fuels, a solution being constituted using fuel cells with H2. Reducing the impact on the environment is aimed at both onboard and aerodrome equipment. This paper proposes the simulation and analysis of an auxiliary power source APU based on a fuel cell. The auxiliary power source APU is a hybrid system based on a PEM-type fuel cell, a lithium-ion battery, and their associated converters. The paper presents theoretical models and numerical simulations for each component. The numerical simulation is performed in MATLAB/SimPower Sys. Particular attention is to the converter system that adapts the parameters of the energy sources to the requirements of the electricity consumers on board the MEA-type aircraft. Power management is performed by a controller based on fuzzy logic.
Author: Tao Wu
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 0
Get Book Here
Book Description
Author: Peng Wang
Publisher: Butterworth-Heinemann
ISBN: 0081007329
Category : Technology & Engineering
Languages : en
Pages : 321
Get Book Here
Book Description
Civil Aircraft Electrical Power System Safety Assessment: Issues and Practices provides guidelines and methods for conducting a safety assessment process on civil airborne systems and equipment. As civil aircraft electrical systems become more complicated, electrical wiring failures have become a huge concern in industry and government—especially on aging platforms. There have been several accidents (most recently battery problems on the Boeing 777) with some of these having a relationship to wiring and power generation. Featuring a case study on the continuous safety assessment process of the civil airborne electrical power system, this book addresses problems, issues and troubleshooting techniques such as single event effects (SEE), the failure effects of electrical wiring interconnection systems (EWIS), formal theories and safety analysis methods in civil aircrafts. Introduces how to conduct assignment of development assurance levels for the electrical power system Includes safety assessments of aging platforms and their respective Electrical Wiring Interconnection System (EWIS) Features material on failure mechanisms for wiring systems and discussion of Failure Modes and Effects Analysis (FMEA) sustainment
