aircraft design pdf

The purpose of this study is to design and develop a new aircraft that complies with the European ultra-light aircraft regulations and the US Light Sport Aircraft regulation. ADS is a free aircraft design software for Windows. It basically lets you analyze aircraft design based on chosen model and parameters. A conceptual framework is necessary in all cases, and it is best suitable for giving an overall view of the expected results. Presenting in one volume the methodologies behind aircraft design, this book covers the components and the issues affected by design procedures. AN INSTRUCTIVE ALGORITHM FOR AIRCRAFT ELEVATOR SIZING TO BE USED IN PRELIMINARY AIRCRAFT DESIGN SOFTWARE Omran Al-Shamma 1* Rashid Ali2 Haitham S. Hasan1 1University of Information Technology and Communications, Baghdad, Iraq 2Sheffi eld Hallam University, UK The longitudinal control is the essential elevator function. April 2014; Authors: Vignesh Meganathan. requirements, and how you can make it better in the next drawing. Book PDF Available. The new edition of this popular textbook provides a modern, accessible introduction to the whole process of aircraft design from requirements to conceptual design, manufacture and in-service issues. paper is to introduce the implementation of multiple winglets of varying lengths on a wing with bell-span (modified) lift José Alexandre Tavares Guerreiro Fregnani, The traditional aircraft design techniques implemented by the industry and academy focus on the evaluation of several disciplines envisioning the optimization of a given objective function. So, a good designer or design team must find an appropriate balance between, design layout and design analysis. Clipping is a handy way to collect important slides you want to go back to later. The main modules of ADS: Analysis: In this module, you can specify datasets for an aircraft and analyze its geometry and performance. Aircraft design is a complex and fascinating business and many books have been written about it. The lift component parallel to the free stream is the induced drag, given by d = l! makes them a promising approach for conceptual-stage aircraft design problems. ResearchGate has not been able to resolve any references for this publication. 1.1. Komarov and others; The Ministry of Education and Science of the Russian Federation, Samara State Aerospace University. wingtip, by 15-20% (Whitcomb winglet). On road the vehicle is designed to run on battery and be propelled by a four cylindered piston engine while on flight thus delivering an uncompromised flight, Flight performance analysis with data-driven mission parameterization: mapping flight operational data to aircraft performance analysis, A STUDY OF THE UTILIZATION OF PANEL METHOD FOR LOW ASPECT RATIO WING ANALYSIS, Cessna Citation X Takeoff and Departure Trajectories Prediction in Presence of Winds, Aerospace Capstone Design: Interactive Initial Sizing Estimates for Increasing Designer Intuition and Mitigating Risk in the Early Stages of Aircraft Conceptual Design, Identification of the Actual Mission Profiles and Their Impact on the Integrated Aircraft and Airline Network Optimization, Aircraft Shape Design Using Artificial Neural Network, ANALYSIS OF MODIFIED LIFTING-LINE THEORY (1933) WITH MULTIPLE WINGLETS, Preliminary design of a radio-controlled micro aircraft for student competition, Integration of Mechanical and Aerospace Engineering Preliminary Design Capstone Courses, DESIGN AND STATIC STRUCTURAL ANALYSIS OF AN AERIAL AND UNDERWATER DRONE, Aircraft Design: A Conceptual Approach, Sixth Edition and RDSwin Student SET, RDS - A PC-based aircraft design, sizing, and performance system, Aircraft Design Optimization on a Personal Computer, Modern Use of Spreadsheet Methods for Aircraft Design, Sizing, and Performance Analysis, RDS Professional: Aircraft Design on a Personal Computer. experience. heir destination by utilizing both road and air routes. flying car capable of transporting two persons and a small amount of luggage from their door step to t. Interested in research on Aircraft Design? - 1 CD-ROM. The basic topics that are essential to the process, such … Provides an introduction to aircraft design, while also exploring the. Academia.edu is a platform for academics to share research papers. Basics of R/C Model Aircraft Design; Download Page; Available PDF files for download: Download File [Title=RC_Model_Aircraft_Design_ALennon_partA.pdf. Each design problem, regardless of how similar it may appear to an earlier aircraft design, is unique and requires a thorough and systematic investigation. [16], ... An aircraft's structural efficiency typically increases with aspect ratio. The method consisted in numerically integrating the aircraft equations of motion for each segment that composed a typical takeoff and departure profile. The combined design of an automobile and aircraft eliminates the need of individual vehicles for road and air, thus reducing the cost and time duration of travel. Aircraft Design: Applied Methods and Procedures by Snorri Gudmundsson, published by Elsevier, Inc. There are dozens of, different activities involved in creating a new air vehicle concept, different specialties, ranging from initial configuration layout to system optimiz. Aircraft design depends on the reliable calculation of numbers but in the end, the, It is difficult to visualize and draw a new aircraft that has a streamlined, It is also true that a nice aircraft drawing is nothing without the analytical results, Writing – and rewriting - this book has been an educating and humbling. As with all engineering, there is an increasing emphasis on design issues in aeronautical engineering. This roadable aircraft falls under integrated style where all the components can be carried within the vehicle and the car can be transformed into an aircraft within few minutes of time vice versa. �:�]�������. For this purpose, the complete aircraft trajectory was divided into five typical segments, including ground acceleration, rotation, transition, climb at constant speed, and climb acceleration. The constraint diagram, created by plotting the required Wing Loading versus Take-off Thrust-to-Weight for all anticipated critical aircraft flight conditions, provided initial sizing information for the aircraft wing area and engine. For the design and development of the aircraft all tools available to the modern engineer have been properly used. This is intended to improve the basic appreciation for the complexity of aircraft structures and systems. The aircraft design process is a loosely defined method used to balance many competing and demanding requirements to produce an aircraft that is strong, lightweight, economical and can carry an adequate payload while being sufficiently reliable to safely fly for the design life of the aircraft. The primary objective, as stated in the RFP, is to design an aircraft that “minimizes operating costs while maximizing the profit for operators1”. %PDF-1.2 %���� NACA 23012 wing of a taper ratio=0.4516 with a geometric twist at n= 8 spanwise locations. By definition, the topic requires intelligent use of aerodynamic knowledge to configure aircraft geometry suited specifically to the customer's demands. ... Γ0circulation at the root The fundamental equation now, given as the following to obtain the geometric twist for an optimum lift distribution. Such rules include the criteria of having the entire aircraft fit in a specific dimensional cylindrical box in unassembled condition, achieving the highest flight score and carrying the highest possible payload with minimum airframe weight, etc. Aircraft conceptual design layout is a, rare talent that takes years to cultivate. distribution and analyze the induced drag differences. 3D CAD models of designs and 2D drawings for dimensional description were prepared. The optimum design point to meet the required performance for missions is found after an iterative trade-off. The weight of the bottom part, top part and the motor holder was computed in CATIA software. The book is available through various bookstores and online retailers, such as www.elsevier.com, www.amazon.com, and many others. where important (design) decisions have to be made that influence product and development costs as well as the product’s performance andproperties[Ullman,2002],[Weilkiensetal.,2015]. The lift component perpendicular to the free stream is approximately equal to l for small downwash angles. An unsupervised machine learning algorithm (DBSCAN) performs a two-step (horizontal and then vertical) clusterization of the principal routes given an O-D pair. Please provide a brief description for the design, ensuring there is a link back to its desired purpose. Drones have been implemented for several application around the world due to its robust technology and ease of operation. Since Iota Air chose a single piston engine, the aircraft will include a full-aircraft parachute. Now customize the name of a clipboard to store your clips. w! $! My greatest pride in the previous editions has been the thanks from, the students who've used the book in their design classes, and the designers of built-and-, flown airplanes who've told me that they made extensive use of my book. Researches also suggest that induced drag reduction can be attained by employing a winglet at the Additionally, when compared to finite volume solutions of the same scenario, the panel method provided a result 20 to 30 times faster than the finite volume solutions. Three parameters were determined during preliminary design, namely: aircraft maximum takeoff weight (W TO); engine power (P), or engine thrust (T); and wing reference area (S ref ). All rights reserved. Filesize=22096KB] If you're wondering, this page is here so we can log download requests and generate a monthly report later. The propulsive efficiency is not dependent on the aspect ratio of the aircraft and is more strongly determined by the choice of engine type/model, intake design, and exhaust design. only thing that actually gets built is the configuration concept shown on the drawing or, CAD file. A total of 38 tests were carried out with the RAFS over a wide range of operational conditions. 69 0 obj << /Linearized 1 /O 72 /H [ 1024 362 ] /L 293204 /E 27927 /N 11 /T 291706 >> endobj xref 69 23 0000000016 00000 n 0000000824 00000 n 0000000879 00000 n 0000001386 00000 n 0000001557 00000 n 0000001741 00000 n 0000002309 00000 n 0000007483 00000 n 0000008411 00000 n 0000008707 00000 n 0000009635 00000 n 0000011268 00000 n 0000011673 00000 n 0000012038 00000 n 0000014680 00000 n 0000015606 00000 n 0000019356 00000 n 0000019815 00000 n 0000020747 00000 n 0000020871 00000 n 0000027636 00000 n 0000001024 00000 n 0000001365 00000 n trailer << /Size 92 /Info 68 0 R /Encrypt 71 0 R /Root 70 0 R /Prev 291696 /ID[<28078160ddfbdadf6c55bbab0005fd9d><28078160ddfbdadf6c55bbab0005fd9d>] >> startxref 0 %%EOF 70 0 obj << /Type /Catalog /Pages 66 0 R >> endobj 71 0 obj << /Filter /Standard /V 1 /R 2 /O (��U'j�Yn6\rT�N�������>/g�@B) /U (�iBOh���\r\r\(Z����Yt��whR�) /P 65472 >> endobj 90 0 obj << /S 207 /T 273 /Filter /FlateDecode /Length 91 0 R >> stream - Samara, 2011. In general, aircraft manufacturers recommend a rotation rate of approximately 3 to 5°/s in order to ensure adequate takeoff performance and avoid a tail strike. Preliminary design of an aircraft starts with initial size and weight estimates. They considered the optimization of an air transportation network fleet around seven U.S. cities. The actual mission profile is introduced using information from automatic dependent surveillance-broadcast (ADS-B). An Airplane Designer: How Can I Become One? In many design paradigms, such analysis does not occur in the conceptual design phase, but later in the preliminary design phase, once the aircraft conceptual layout is set. This value is determined by the obstacle clearance requirement for commercial aircraft, ... Running the physics-based model under the nominal condition yields fuel burn estimation RMSE values close to 20% for the three sectors, denoted as the blue inverted triangles shown in Figs. lcos$! Table 2.1: Design Requirements1 Description Requirement Certification 14 CFR Part 23 Noise Limit Part 36 Sec. Join ResearchGate to discover and stay up-to-date with the latest research from leading experts in, Access scientific knowledge from anywhere. To validate that this method, it was applied to 2 elliptical planforms with constant thickness where experimental force balance data was available. Information on the actual mission's that the designed aircraft will perform is not considered at a realistic level in an environment where the major efforts are applied in the dis-cipline's evaluation. The third step in the design process is the detail design. Tables 2 and 6 Two different types of aircraft designs were considered in demonstrating this method to students. The pre-processing and post-processing blocks of the machine learning framework use a flight phase identification algorithm, 1. to simplify the distance evaluation between routes (input for DBSCAN algorithm) and, 2. to obtain data for the definition of the final route missions used in the aircraft evaluation framework. Additionally, the same 2 wings were analyzed using a finite volume solver to compare pressure distributions and to demonstrate the difference in magnitude of solution times. lsin$! The validation of the methodology was evaluated with a qualified Research Aircraft flight Simulator (RAFS) of the Cessna Citation X. Following the categorization by the Federal Aviation Administration (FAA) and Eurocontrol [11] , these flight performance models can be divided into four classes based on the physics mechanism, namely the six degree-of-freedom trajectory calculation [12,13] , the point-mass model [3,14,15] , the macroscopic behavior modeling approach, and the tabular data approach. get you started and will provide a resource of material throughout your career. Designing an aircraft is a complex, multifaceted process that embraces many technical challenges in a multidisciplinary envi-ronment. adapted to the Common Parametric Aircraft Configuration Scheme (CPACS), used as a data exchange format to enhance the interaction between them. The basic topics that are essential to the process, such as aerodynamics, flight stability and control, aero-structure, and aircraft performance are reviewed in various chapters where required. It contains design methods, illustrations, tips, explanations and equations, and has extensive appendices with key data for design. Whichever aspect you may lean towards, the book should hel. By definition, the topic requires intelligent use of aerody-namic knowledge to configure aircraft geometry suited specifically to a customer’s demands. l! The optimization is carried out by a framework that combines dynamic programming, nonlinear programming, and linear integer programming. However, the complexity of an aircraft and the tight safety regulations required make it a very expensive and long process. To capture the effect of the leading edge vortex, a panel method code was used with an extended definition of the Kutta condition along portions of the leading edge inducing a vortex to shed from the leading edge and flow aft just inside the leading edge. In this scope, the concept generations of multiple designs for the micro aircraft with appropriate dimensions were done. The panel method can reasonably model the lift and induced drag characteristics of low aspect ratio wings. These apply equally to. For comparison purposes, the resulting forces and moments from both computational methods and experimental testing were plotted over a range of angles of attack. The objective of this paper is to present a practical method developed at the Laboratory of Applied Research in Actives Controls, Avionics, and AeroServoElasticity (LARCASE) for calculating takeoff and departure trajectories of a Cessna Citation X. S�z췑�=�\�&x!� ���Rǿ7�a�/p�pL�q _�Cܹ1���q���lNY��R1��Z��k With this in mind, the modified panel method application strategy lends itself to preliminary design phases of low aspect ratio wings where the level of detail does not warrant finite volume analysis and solution speed has higher priority. Comparison results showed that the trajectory data predicted by the different algorithms matched the trajectory data obtained from the RAFS with less than 5% of relative error. This textbook presents the process of aircraft conceptual design as seen in industry aircraft design groups. The use of empirical relations, wind tunnel experiments, and finite-volume simulations are the dominate tool for design for these LAR wings [1], ... Another approach to evaluate the takeoff and initial-climb trajectory of an aircraft is to use empirical or semiempirical models. First, in a section aimed at the student of aircraft design, the reader is introduced to various aircraft components. Download Free eBook:Aircraft Design: A Conceptual Approach (Repost) - Free chm, pdf ebooks rapidshare download, ebook torrents bittorrent download. Filesize=22531KB] Download File [Title=RC_Model_Aircraft_Design_ALennon_partB.pdf. Conventional panel methods fail to capture the leading edge vortex (LEV) that is shed by wings with low aspect ratios, typically below 2 depending on planform. In this work, the airline network allows direct routing (i.e. As a part of the research conducted, numerical analysis has been performed on a This project uses an innovational quadcopter design with a new streamlined structural geometry. Ludwig Prandtl’s modified lifting line theory explains the reduction in induced drag by 11% in comparison to elliptic lift Aircraft Design explores the conceptual phase of a fixed-wing aircraft design project. Presenting in one volume the methodologies behind aircraft design, this book covers the components and the issues affected by design procedures. ALL SUCH ‘FREE DOWNLOAD’ COPIES ARE ILLEGAL! During this process, the aircraft mission is selected in accordance with the OEM's and Airlines requirements and represented as a predefined mission in the aircraft design algorithms. The compact structure consists of wings which remain folded on road and gets expanded when required for flight. Aviation program overruns and problems with new aircraft are more common than desired, prompting some calls for a new approach to aircraft designs. 6 with a first-order Gaussian curve, the friction coefficient was determined to be 0.018 for a dry runway, 0.027 for a wet runway with a water depth of 5 mm, and finally 0.038 for a runway with a water depth of 12 mm. Civil Jet Aircraft Design [Jenkinson] on *FREE* shipping on qualifying offers. You just clipped your first slide! Read full-text. Aircraft Conceptual Design resources for industry, academia, and research of airplane and spacecraft design, including the textbook AIRCRAFT DESIGN: A Conceptual Approach, the RDS design software, the book Simplified Aircraft Design for Homebuilders, Design Short Courses, and aerospace-related books. book’s title refers to a design process centered around a realistic concept layout. The aircraft is a two-seater model, oriented towards fast and economic travelling. Overall, the results demonstrate that a modified panel method could be used during the preliminary design phases for low aspect ratio wings. (PDF) Aircraft Design-A Conceptual Approach (Daniel P. Raymer) | la bv - Academia.edu Academia.edu is a platform for academics to share research papers. REC; Download full-text PDF Read full-text. The very complexity and dynamic nature of the subject means that no one book can do it justice. The complete aircraft trajectory was obtained by combining these segments in a specified order depending on the departure procedure profile. ‘Civil Jet Aircraft Design’ is the definitive textbook on this. All content in this area was uploaded by Daniel Raymer on Jan 26, 2019, This book is copyright and is not legally. It is my sincere wish that it helps aspiring aircraft designers to “learn the, ropes” more quickly. The general process can be divided as shown below: The purpose of the appendices denoted by C1 through C5 is to provide additional information on the design of selected aircraft configurations, beyond what is … Bluntly stated, if, drawing, you don't have an aircraft design. … This book, therefore, will primarily act as an introduction to the whole field of aircraft design leading towards the subjects summarized in Fig. The gross weight estimate is then determined using an iterative process. Its creation is not a trivial task of drafting based upon the analysis results, but, rather it is a key element of the overall design process and ultimately determines the, performance, weight, and cost of the aircraft. Follow @DanRaymerPhD: New AIAA Article! The project studies presented in this book merely serve as examples of how the design process has been followed in the past by other teams faced with the task of solving a unique problem in aircraft design. Download citation. Designs often differ depending on the demands of the consumers and manufacturers, economic constraints, outlook preference, safety protocol, and more. to support it, and it will be a much better design if clever optimization methods are, employed. The goal of this project is to design a personal aerial vehicle (PAV) – Roadable aircraft i.e. Well, at the end of the … Then, the chapter details the pros and cons of a number of configuration styles. 1.4 The Book: What Is Here and How It Is Organized, 2.4 Integrated Product Development and Aircraft Design, Chapter 3 Sizing from a Conceptual Sketch, Chapter 4 Airfoil and Wing/Tail Geometry Selection, Chapter 5 Thrust-to-Weight Ratio and Wing Loading, 5.4 Selection of Thrust to Weight and Wing Loading, Chapter 8 Special Considerations in Configuration Layout, Chapter 9 Crew Station, Passengers, and Payload, Chapter 10 Propulsion and Fuel System Integration, Intermission: Step-by-Step Development of a New Design, 15.4 Additional Considerations in Weights Estimation, Chapter 16 Stability, Control, and Handling Qualities, Longitudinal Static Stability and Control, Chapter 17 Performance and Flight Mechanics, 17.1 Introduction and Equations of Motion, 17.10 Other Fighter Performance Measures of Merit, 20.10 Electric Aircraft Run-Time, Range, Lo, Chapter 23 Design of Unique Aircraft Concepts, 23.2 Flying Wing, Lifting Fuselage, and Blended Wing Body, Appendix E Typical Engine Performance Curves, Appendix F Design Requirements and Specifications, Aircraft Design is a challenging, rewarding, and fun career. Simplified models of aircraft performance (Breguet Equations. However, for aircraft such as the Cessna Citation X, this value may be higher due to relatively small inertia, ... By approximating the error distributions in Fig. also be purchased directly from the publisher, at these links. Introduction to Aircraft Design Induced drag (2) U! The aircraft is designed with the aim to compete in the SAE Aero Design Student Competition. This work presents a preliminary design study of a radio-controlled micro aircraft. This aerodynamic phenomenon contributes to a significant amount of the lift of these wings and the result is a drastic underestimation of the lift characteristics when analyzed by conventional panel method. The primary motive of the design is to fulfil the standards of a PAV set by NASA. PDF | On Sep 30, 2018, Daniel Raymer published Aircraft Design: A Conceptual Approach, Sixth Edition | Find, read and cite all the research you need on ResearchGate. For each segment, detailed algorithms to solve and integrate the equations of motion using an Euler scheme were designed. These activities can be grouped into two equally important aspects of aircraft design: differing aspects attract different types of people. no hub is forced). The Aircraft Design Process. The advent of aviation • National Advisory Committee for Aeronautics – 1915, foundation of N.A.C.A. This study demonstrates the applicability of using a modified application strategy of panel method to analyze low aspect ratio wings at preliminary design phases. Certain people love playing with, numbers and computers, whereas others can't stop doodling on every piece of paper, This book offers a balanced overview of these two aspects of design, integrated, together and presented in the manner typically seen in an aircraft design project at a, major aerospace company. The climb segment starts at the 35-ft altitude, which is at the end of the takeoff phase. The integrated airline fleet and network optimization are performed by a framework architecture that embeds (inside the aircraft optimization framework) a linear programming algorithm responsible for obtaining the potential optimal networks considering the demand (bidirectional) and capacity constraints. No prototypes were manufactured due to the Covid-19 situation. The aircraft framework is composed of several disciplines (e.g. In this project we would like to implement drones for underwater as well as aerial surveillance at our coastline and further extend its application for detection of underwater air crashes and ship wrecks. It supplies full coverage of the design elements of methods engineering methodologies. The design process for an aircraft can be seen as very similar to other engineering products. Aerodynamics, Performance, etc.) An heuristic based genetic algorithm is used to solve the system of systems optimization. 2020-2021 Aircraft Design - Introduction & History 23. Different designs were performed by different groups of students following the rules given in the SAE 2017 competition document. This method loses applicability beyond the stall point where the leading edge vortex breaks down and oversimplifies pitching moment relation to angle of attack. Download full-text PDF. CONCEPTUAL AIRCRAFT DESIGN = Концептуальное проектирование самолетов [Electronic resource]: Electronic Textbook /V.A. Although to some extent good designers are, “born, not made,” the proven methods and best practices of aircraft configuration layout, can be taught and are covered here in the first half of this book. The new design is validated for its successful implementation through stress analysis using ANSYS, also suitable material for fabrication is selected by comparing five other materials. Designing an aircraft is a complex multifaceted process embracing many technical challenges in a multidisciplinary environment. http://www.amazon.com/exec/obidos/ASIN/1624104908/danraymesaircrde, https://arc.aiaa.org/doi/book/10.2514/4.104909, Author's Note Concerning Use of Metric Weight Units. The “Conceptual Approach” mentioned in the. aerodynamic shape and an efficient internal layout and yet satisfies an incredible, of real-world constraints and design specifications. © 2008-2020 ResearchGate GmbH. �j��yKT�va@�%g�E\��4\��/SRA� In this paper, the impact of the real mission profile is evaluated inside the integrated aircraft and airline network simultaneous optimization process, considering ATM constraints. Underwater drones must consider important factors such as floatability and buoyancy which challenges the structural integrity and power requirements of the drone. ""! - Electronic text and graphic data (1,1 Mb). Design Brief Design an aircraft that can be used in search and rescue. The weight estimation procedure is adopted from. In addition, basic paper prototypes of the designs which were helpful to visualize the aircraft were constructed. A comprehensive approach to the air vehicle design process using the principles of systems engineering Due to the high cost and the risks associated with development, complex aircraft systems have become a prime candidate for the adoption of systems engineering methodologies. The second half of this book covers analysis and, optimization methods that will tell you if the design works, if it meets its design. In chapter 4, aircraft preliminary design – the second step in design process – was introduced. The aircraft must be able to get into tight places and must be able to search large areas for a missing person, but it can take any form. I. Nomenclature ADS-B = automatic dependent surveillance broadcast ATM = air traffic management BFL = balanced field length, [m] CAD = computer aided design CFD = computational fluid dynamics d = actual distance of route (i,k), [nm] DBSCAN = density-based spatial clustering of applications with noise DOC = direct operational cost, [USD] DOF = degrees of freedom g = vector of equality constraints GCD = great circle distance, [nm]. The primary motive of this The entire frame is designed using CATIA. AIRCRAFT DESIGN PROJECT -I Heavy Business Jet. Aircraft engineering is a process that begins with model design. traditional drafting table drawings and to modern computer-aided design. distribution. A database from FR24 is used to obtain information of 6 months of flights between ten of the principal destinations of the European Union network. Aircraft Design explores fixed winged aircraft design at the conceptual phase of a project. Provides a Comprehensive Introduction to Aircraft Design with an Industrial Approach This book introduces readers to aircraft design, placing great emphasis on industrial practice. It includes worked out design examples for several different classes of aircraft, including Learjet 45, Tucano Turboprop Trainer, BAe Hawk and Airbus A320. This book presents the entire process of aircraft design based on a systems engineering approach from conceptual design phase, through to preliminary design phase and to detail design phase.

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