DOCSLIB.ORG

Nasa.Gov/Search.Jsp?R=19740027166 2020-03-23T02:10:34+00:00Z

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text
Nasa.Gov/Search.Jsp?R=19740027166 2020-03-23T02:10:34+00:00Z https://ntrs.nasa.gov/search.jsp?R=19740027166 2020-03-23T02:10:34+00:00Z NASA CR-134596 FRACTURE CONTROL METHODS FOR SPACE VEHICLES Volume I Fracture Control Design Methods BY A.F. Liu REPRODUCED BY NATIONAL TECHNICAL INFORMATION SERVICE U. S. DEPARTMENT OF COMMERCE SPRINGFIELD, VA. 22161 Cr; OF: PI *z1-1 m Ff 1x1 t.Q 1-1 Prepared for -4 = i a), mkrzr * I.nmu.5dw NATIONAL AERONAUTICS AND SPACE ADMINISTRATION =lIJ-1 I-I U .ri rn+mor! r Filffiid I IrlII-U Pi U U 4 1-rl 5 5 t PIO-Qh NASA Lewis Research Center Contract NAS 3-16765 FRACTURE CONTROL METHODS FOR SPACE VEH l CLE S Volume I Fractu re Control Design Methods by A. F. Liu Contract NAS3- 16765 NASA Lewis Research Center Cleveland, Ohio August 1974 * 1 Report No 2 Government Access~onNo 3 Reclptent s Cataloq No NASA CR-134596 4 Tttle and Subt~tle 5 Report Date Fracture Control Methods for Space Vehicles Volume I, August 19 74 Fracture Control Design Methods 6 Perforrntng Organlzatton Code 7 Author(s1 A.F. Liu 8 Perforrn~ngOrganlzatlon Report No SD 73-SH-0171-1 9 Perform~ngOrgantzatlon Name and Address 10 Work Unit No Space Division Rockwell International Corporation 11 Contract or Grant No Downey, CA 90241 NAS 3-16765 12 Sponsor~ngAgency Name and Address 13 Type of Report and Pertod Covered National Aeronautics and Space Administration Contractor Report .June 1972 through March 1974- 21000 Brookpark Rd. 14 Sponsortng Agency Code Lewis Research Center, Cleveland, OH 44135 15 Supplementary Notes Project Manager, Gordon T. Smith NASA Lewis Research Center Cleveland, OH 44135 16 Abstract This report is concerned with a systematic approach for applying methods fcr fracture control in the structural components of space vehicles. Four niaj~r steps are required to complete the fracture control sequence. The first step is to define the primary load-carrying structural elements and the type of load, environment, and design stress levels acting upon them. The second step is to identify the potentiai fracture-critical parts by means of a selection logic flow diagram. The third step is to evaluate the safe-life and fail-safe capabilities of the specified part. The last step in the sequence is to apply the control procedures that will prevent damage to the fracture-critical parts. The fracture control methods discussed herein include fatigue design and analysis methods, methods for preventing crack-like defects, fracture mechanics analysis methods, and nondestructive evaluation methods; however, emphasis is placed on the fracture mechanics analysis methods. To illustrate the use of fracture mechanics methodology, an example problem is presented for evaluation of the safe-crack-growth capability of the Space Shuttle crew compartment skin structure. PRICES SU?J:- - 17 Key words (Suggested by Author(s) 18 Dlstr~buttonStatement Fracture Mechanics Space Vehicle Structure Unclassified, Unlimited Fracture Control Procedures 19 Secur~tyClasstf (of thts report) 20 Securtty Class~f (of thts page) 21 No of Pages 22 Prtce' Unclassified Unclassified The work tlescribcd in this report was pc,rfor~ncdby the Spdce I>i\.ision of Rockwcll Intcrnat~onalCorporation under Contract NAS 3- 1076 5, T'racture Control Methods for Space Shuttle Vt.hiclcs, for the 1,cn.i~1lc.st arc]) Ccnter of the National Aeronautics and Spacc Aclministration. TJle ~n\lt.stigatjon\(as contlucted undcr the technical direction of Mr. Cortlon T. St111th of NASA/ LeRC. The project study manager at the Space I>i\~isjonof f~ocl<~'cll International Corporation was Mr. A. F. I,iu, nit11 Dr. Paul C. I'aris of Dcl Research Corporation and Dr. Matthew Crca~c,rof JIc1 West Associates, Inc. , acting as primary technical consultants, This report consists of three volumes: Volume I. Fracturcl Control Design h/lcthorls (prc,pared by A. F. 1,iu) Volume 11. Assessment of Fracturc Mech;rnics Tectinology for Space Shuttlc Applications (prepared by R. M. Ehret) Volume 111. Space Shuttle Configurations (prepared by A. 1'. IJiu and E. .J. Mulcahy) Mr. .Jan~esE. Colliprjest, Jr., provided overall technical guidance in the preparation of Volun7e 11. Mr. Eclward .T. Mulcally and Mr. A.S. Muslcman contrj1)utcd significantly to the preparation of Section 1. 1 (Space Shuttle Vehlcle Structural Ilescriptlon) of Volunle I. Mr. John Malnon and Mr. F. Stuckcnbcrg aided substantially in the preparation of the. nondcstruc~iveevaluation sectlons in Volumes I and 11. Mr. K. E. O'Brien and Mr. R.M. Ehret contributc~cl, respcctively, Section 2. 2 (Prevention of Cracks and Crack-Like Defects In Shuttle Vehicle Structure) and Section 2. 3. 8 (Required Material Properties Data for Space Shuttle Fracture Mechanics Analysis) of Volume I. Dr.Matthe\~- Creage r contri butcrl Sc,ct~on2. 3. 6 (Failure Under Complex Loading Conditions) and Section 2. 3. 7. 4 (Damage, Tolerance An:~lysisfor Pressure Vessels) of Volume I and Sectlon 2. 2 (Thin Sheet Behavior) and a discussion of fracture behavior under corn1)jned in-plane loading in Stction 1.2 (Lintbar Elastic Con- cepts of Fracturc Behavior) of Volumc 11. Mr. R. W. Westrup prepared the original proposal response to the RFI' and established ttic basic frame work for tile study program. The managerial guidance provided by Mr. R. I?. Olsen, EnKinccringManager, Materials and I'rocesses, Spacc Division, is acknoq,lc~d~edby thc authors. CONTENTS Section Page INTRODUCTION . 1 1. 0 APPRAISAL OF SPACE SHUTTLE VEHICLE STRUCTURES. 1. 1 Space Shuttle Vehicle Structural Description . 1.1.1 SolidRocketBooster . 1. 1.2 External Tank . 1. 1. 3 Mid Fuselage . 1. 1. 4 Wing . 1. 1. 5 Forward Fuselage and Crew Compartment, 1. 1. 6 Aft Fuselage . 1. 1. 7 Vertical Stabilizer . 1. 1. 8 Landing Gear . 1. 2 Critical Part Selection Logic. 1.2.1 LossofAssembly(Step4) . 1. 2.2 Loss of Vehicle (Step 6). 1. 2. 3 Redundant Member or Multiload Path (Step 5) . 1. 2. 4 Accessibility Requirements (Step 9) . 1. 2. 5 Evaluation of Potentially Fracture- Critical Parts (Step 7). 1. 2. 6 Critical Part Selection Logic Application Examples . FRACTURE CONTROL METHODS . 2. 1 Fatigue Design and Analysis Methods . 2. 1. 1 Fatigue Performance . 2. 1. 2 Detail Design Considerations . 2. 1. 3 Fatigue Analysis Methods . 2.2 Prevention of Cracks and Crack-Like Defects in Space Vehicle Structure . 2. 2. 1 Administrative Controls and Activities . 2.2.2 Technical Activities . 2. 3 Fracture Control Methods for Initially Cracked Structures . 2. 3. 1 Safe-Crack-Growth and Fail-Safe Structures . - . PRECEDING PAGE BLANK. NOT FILD' ' - Section Page 2. 3. 2 Classification of Space Shuttle Structural Elements . 2.3.3 MonolithicStructure . 2. 3. 4 Crack Arrest Structure . 2. 3. 5 Multiple Element Structure . 2. 3. 6 Failure Under Complex Loading Conditions . 2. 3. 7 Failure of Pressure Vessels and Shells 2. 3. 8 Required Material Property Data for Space Shuttle Fracture Mechanics Analysis . 2. 3.9 Recommendations on Fracture Mechanics Research and Development 2.4 Nondestructive Evaluation . 3. 0 FRACTURE CONTROL PROCEDURES . 3. 1 Fracture Mechanics Procedure , 181 3. 2 An Example Problem 185 3. 2. 1 Design Stress Level, Material and Structural Dimensions . 185 3.2.2 Crack Geometry . 187 3.2. 3 Stress Intensity Factors . 19 0 3.2.4 Initial Crack Lengths . 194 3. 2.5 Crack Growth Predictions ' . 19 4 4. 0 SUMMARY AND RECOMMENDATIONS . 203 5. 0 REFERENCES. 205 APPENDIX SYMBOLS AND SUBSCRIPTS . 215 ILLUSTRATIONS Figure Page Critical Part Selection Logic . Fracture Control Program Elements . Elements for Fatigue Design and Analysis . Double-Scarf Joint Specimen . Double-Shear Joint Specimen . Stepped Double Shear Joint Specimen . Plain- Scarf Joint Specimen . Single- Shear Joint Specimen . Continuous Member Tension Design . Examples for the Definition of GAG Cycle . Comparison of Fatigue Crack Growth Characteristics for Monolithic Structure and Crack Arrest Structure Comparison of Fatigue Crack Growth Characteristics for Monolithic Structure and Multiple Element Structure . Crack Growth Characteristics Under Monotonic Increasing Load . Cross-Sectional Views of Common Crack Geometries Through- t he-Thickness Crack Loaded in Tension . Stress Intensity Factors for Eccentrically Cracked Plate . Through-the-Thickness Edge Crack in a Plate Loaded in Tension . Failure Analysis Using an R-Curve . R-Curves for Aluminum Alloys . Failure of Aluminum Alloy Sheets Predicted From R-Curve . Fracture Toughness of Bare 2024-T3 Sheets . Geometries of Truncated Elliptical Cracks . Front Free Surface Influence Factor Ml . Front Surface Influence Factor M11/4 for a/c I1 . Front Surface Influence Factor Mlf/+-for a/c r 1 . Change of Flaw Shape in Propagation of Surface Crack S.urface Flaw Fatigue Crack Propagation Data . Free Surface Correction Factor for Corner Flaw . Crack or Cracks Emanating F'rom a Hole . - vii - Figure Page Flaw. Shape Factor MI @ . Bowie's F'actors for Influence of a Hole . Stress Illtensity Factor Versus Crack Length for a Lug . Stress Intensity Factor for a Pin-Loaded Hole . Through- the- Thickne ss Cracks in Skin- Stiffened Panel . Strc ss Intensity Analysis of Unstiffened and Stiffened Structure . Stress Intensity Factor for Crack Extending Equally on Both Sides of Point Midway Between Two Stringers (NASA TR R-3 58) . Stress Intensity Factor for Crack Cxtending Equally on Both Sides of Stringer (NASA TR R-358) . Stiffener Stiffness Parameter as a Function of Effective Stiffener Area Stiffener Efficiency Factor for a One-Bay Crack as a Function of Stiffener Stiffness Parameter . Stiffener Efficiency Factor for a Crack Extended Symmetrically on Both Sides of a Stringer . Effects of Applied Stress Levels on the Stiffener Efficiency. The Effects of Broken Stiffener and Stiffener Yielding on Crack Tip Stress Intensity . The Effect of Broken Stiffener on the Stress Intensity Factor . The Effect of Broken Stiffener on the Stress Intensity Factor . Stiffener Efficiency Factor for a Two-Bay Crack With a Center Broken Stiffener .
Load more

Recommended publications
  • FRENCH PRE-WAR REGISTER Early Companies: CMA – Compagnie Des Messageries Aeriennes. Commenced 1.5.19 Paris-Lille; Paris-Londo
    FRENCH PRE-WAR REGISTER Version 120211 Early Companies: CMA – Compagnie des Messageries Aeriennes. Commenced 1.5.19 Paris-Lille; Paris-London 26.8.19 (JV with Handley Page Transport). CGT – Compagnie Generale Transaerienne. Formed in 1909 to operate airships. Op Paris-London in 1920 in JV with AT&T. CGEA – Compagnie des Grands Express Aeriens. Formed 5.19 by Lt Villier and other air force officers. Paris-London wef 5.3.20. Compagnie Latecoere. Formed 24.12.18 to fly Toulouse-Barcelona; to Alicante 25.2.19; to Rabat 20.3.19; to Casablanca 1.9.19. CAF – Compagnie Aerienne Francaise. Nimes-Nice wef 17.4.19; Suspended 8.20. Aero Transport Compagnie Ernoult. Late 1919 operating Salmsons and Sopwiths Bordeaux-Agen-Toulouse-Narbonne- Bezier-Montpellier. Also op associate as Aero Publicite. TASO – Compagnie des Transports Aeriens du Sud Ouest. Formed 7.19; renamed Societe Franco Bilbaise des Transports Aeriens in 1920 (?). Biarritz-Bordeaux 8.19; to Sans Sebastian 9.19. Bayonne-Bilbao wef 13.6.20 Lignes Farman. Paris-London. To Casablanca & Port Etienne 11.8.19; to Copenhagen 13.8.19. Paris-London 9.19; to Briussels Compagnie Aero Transport. Paris-Geneva 1.7.20 in associateion with L’Ecole Aero Suisse (Sopwiths) CFRNA – Compagnie Franco Roumaine de Navigation Aerienne – formed 23.4.20. Paris-Strasbourg 20.9.20 (Salmson/Potez); to Prague 7.10.20. CGA – Compagnie Generale Aeronautique. Formed 1920 Societe des Transports Aeriens Guyannais. Formed 1919 (Levy seaplanes) St Laurent-Snini-Cayenne F-"ALxx" – Lignes Aeriennes Latecoere Note – Cie Generale d’Entreprises Aeronautiques formed 6/21 by Latecoere) F-ALAA Latecoere Breguet 14 (1) 6.20 [[173] M Latecoere, Toulouse F-ALAE Latecoere Breguet 14 (26) 6.20 [198] M Latecoere, Toulouse F-ALAI Salmson 2.A2 (31) 6.20 (141) M Latecoere, Toulouse.
    [Show full text]
  • TMS-MC-015 Revision 30 Page 2 of 104 01 April 2016 * REVISED ** ADDED ______
    Lockheed Martin Aeronautics Company Supplier Tooling Manual (Tool Manufacturing Specification - Material Control - 015) TMS-MC -015 Applicable to FORT WORTH – MARIETTA - PALMDALE Sites To the extent specified herein REVISION 30 CONTROLLED AND APPROVED BY: Lockheed Martin Aeronautics Company Supplier Quality Management May 2016 IMPORTANT NOTICE: A hard copy of this document may not be the document currently in effect. The current version is ALWAYS the version on the LOCKHEED MARTIN network. TMS-MC-015 Revision 30 Page 2 of 104 01 April 2016 * REVISED ** ADDED _____________________________________________________________________________ TABLE OF CONTENTS PART I. AIRCRAFT ITEMS AND TOOLING - SELLER REQUIREMENTS *1.0 SCOPE Page 5 *2.0 TOOLING DEFINITIONS Page 6 *3.0 INTERCHANGEABLE-REPLACEABLE (I/R) Page 10 4.0 “TO MATCH” HOLE PATTERNS AND OTHER I/R FEATURES Page 10 *5.0 CONTROL OF RECORDS FOR BUYER FURNISHED TOOLING Page 10 *6.0 REPORTING REQUIREMENTS Page 11 *7.0 CONTROL OF BUYER-FURNISHED TOOLS Page 12 8.0 TOOL QUALITY CODE CATEGORIES Page 13 9.0 TOOL PROTECTION AND STORAGE REQUIREMENTS Page 14 *10.0 SHIPPING AND RECEIVING INSTRUCTIONS Page 14 *11.0 TOOLING PERIODIC INSPECTION AND RE-VERIFICATION Page 16 (PI/V) *12.0 TOOLING PERIODIC INSPECTION AND RE-VERIFICATION Page 18 (PI/V) RECORDS 13.0 BUYER FURNISHED AND SELLER TO SELLER TRANSFER OF TOOLS Page 19 14.0 LOCKHEED MARTIN SUBCONTRACT SOURCE BOOKS Page 19 *15.0 BASIC PRINCIPLES FOR PRODUCTION USE OF TOOLING Page 19 PART II. MANUFACTURED SPECIAL TOOLING ONLY – SELLER REQUIREMENTS 1.0 GENERAL Page 20 *2.0 NON-RECURRING TOOL MANUFACTURING Page 20 3.0 SPECIAL TOOLING INSPECTION AND QUALITY REQUIREMENTS Page 21 *4.0 TOOL IDENTIFICATION AND SHIPPING REQUIREMENTS Page 23 5.0 PROCESS FOR TRANSFER OF TOOL DESIGNS FROM SELLER Page 24 TO BUYER 6.0 SEALING CRITICAL LOCATORS Page 24 *7.0 DUPLICATE TOOL MANUFACTURING Page 24 8.0 INTERCHANGEABLE- REPLACEABLE (I/R) DESIGN AND MANUFACTURING Page 24 9.0 NON (I/R) DESIGN AND MANUFACTURING Page 25 PART III.
    [Show full text]
  • Les Hydravions CAMS
    Publicité de la CAMS, « la plus grande firme française d’hydravions », parue dans la revue L’Aéronautique n° 138, novembre 1930. (Collection de l’auteur). 1 Parallèlement, Santoni entreprend en Italie, un Naissance des Chantiers pays dont il est originaire, la création d’une impor- tante société pour fabriquer sous licence les avions Aéro Maritimes de la d’Henry et Maurice Farman, mais il y introduit aussi les produits français qu’il connaît bien : héli- Seine (CAMS) ces Régy et Chauvière, vernis Emaillite, et divers instruments de bord. Le 5 mai 1913, il crée à Va- Laurent-Dominique Santoni est né à Genève en rèse en Italie une société pour la construction Suisse le 19 février 1877. Après des études primai- d’hydravions, la Société anonyme de construction aéro- res et secondaires en France, parlant couramment nautique Savoïa. l’Italien et l’Anglais, (pour les uns il est Lawrence Santoni, pour les autres Lorenzo Santoni), il achève sa formation en décrochant un diplôme d’ingénieur. A vingt-deux ans, il suit avec passion le meeting de Reims et veut devenir aviateur. En 1910 à Port-Aviation (communes de Juvisy-sur- Orge et Viry-Châtillon) où s’ouvrent les premières écoles de l’air, il fréquente les premiers aviateurs, Louis Gaudart, chef pilote Voisin, le comte de Saint-Germain, chef pilote de l’école Donnet sur FBA type C aux couleurs de la marine italienne (1915). Le type C appareil Blériot, Pauwels et Bobba, les pilotes de italien construit chez S.I.A.I.-Savoïa était propulsé par un moteur fixe l’école d’Ambroise Goupy, et Emile Dubonnet, le à six cylindres en ligne Isotta-Fraschini de 120 ch.
    [Show full text]
  • TSR2 with HINDSIGHT
    TSR2 with HINDSIGHT Edited by Air Vice-Marshal A F C Hunter CBE AFC DL 2 TSR2 WITH HINDSIGHT The opinions expressed in this publication are those of the contributors concerned and are not necessarily those held by the Royal Air Force Historical Society. Copyright © 1998: Royal Air Force Historical Society First published in the UK in 1998 by the Royal Air Force Historical Society British Library Cataloguing in Publication Data available ISBN 0-9519824 8 6 All rights reserved. No part of this book may be reproduced or transmitted in any form or by any means, electronic or mechanical including photocopying, recording or by any information storage and retrieval system, without permission from the Publisher in writing. Photographs courtesy of BAe North West Heritage Group and Rolls-Royce plc, Bristol Typeset and printed in Great Britain by Fotodirect Ltd, Brighton Royal Air Force Historical Society TSR2 WITH HINDSIGHT 3 s of all three pilots who flew the aircraft. flew who pilots three of all s A fine shot of TSR2 in flight bearing the signature the bearing in flight TSR2 of shot fine A 4 TSR2 WITH HINDSIGHT Contents Page Foreword 6 Air Vice-Marshal A F C Hunter CBE AFC MA LLB DL Chairman’s Introductory Remarks 7 Marshal of the Royal Air Force Sir Michael Beetham GCB CBE DFC AFC DL Section One Setting the Scene 9 Wing Commander R P Beamont CBE DSO* DFC* FRAeS DL The History of the Project and the Operational 12 Requirement Group Captain W A Mears BA A System Study of TSR2 16 Wing Commander G B Wilson BSc CEng MIEE Discussion 26 Section Two
    [Show full text]
  • Aircraft Stability and Control to Aerospace Engineering Students
    A LONELY IMPULSE OF DELIGHT DROVETOTHISTUMULTINTHECLOUDS; WILLIAMBUTLERYEATS, ANIRISHAIRMANFORESEESHISDEATH L’AVION AVAIT GAGNÉ D’UN SEUL COUP, À LA SECONDE MÊME OÙ ILÉMERGEAIT,UNCALMEQUISEMBLAITEXTRAORDINAIRE.PAS UNE HOULE NE L’INCLINAIT. COMME UNE BARQUE QUI PASSE LA DIGUE,ILENTRAITDANSLESEAUXRÉSERVÉES.LATEMPÊTE, AU-DESSUSDELUI,FORMAITUNAUTREMONDEDETROISMILLE MÈTRESD’ÉPAISSEUR,PARCOURUDERAFALES,DETROMBESD’EAU, D’ÉCLAIRS,MAISELLETOURNAITVERSLESASTRESUNEFACEDE CRISTALETDENEIGE. ANTOINE DE SAINT-EXUPÉRY, VOLDENUIT THEREWILLBETIMETOAUDIT THEACCOUNTSLATER,THEREWILLBESUNLIGHTLATER ANDTHEEQUATIONWILLCOMEOUTATLAST. LOUISMACNEICE, AUTUMNJOURNAL MICHAELCARLEY AIRCRAFTSTABILITY ANDCONTROL This is not a textbook This is not a textbook and should not be read as one. It is a set of notes for a third year unit at the University of Bath, introducing aircraft stability and control to aerospace engineering students. The aim is to develop an understanding of concepts, but only if the notes are read in conjunction with other material, and combined with attendance at lectures. These notes will not be much use on their own. You will have to work hard on ideas which will not be obvious, and were not obvious to the smart people who developed them. You will often feel stupid and confused, and you will wonder why you are doing this. You are doing this because it is worth it: you are taking on a difficult topic which has confused bright people for over a century, but in which it is possible to make a contribution. Feeling stupid means you are working on something
    [Show full text]
  • Uncontrolled Flight Into Terrain, ABX Air (Airborne Express) Douglas DC
    PB97-910405 NTSB/AAR-97/05 DCA97MA016 NATIONAL TRANSPORTATION SAFETY BOARD WASHINGTON, D.C. 20594 AIRCRAFT ACCIDENT REPORT UNCONTROLLED FLIGHT INTO TERRAIN ABX AIR (AIRBORNE EXPRESS) DOUGLAS DC-8-63, N827AX NARROWS, VIRGINIA DECEMBER 22, 1996 F 6822A I The National Transportation Safety Board is an independent Federal agency dedicated to promoting aviation, railroad, highway, marine, pipeline, and hazardous materials safety. Established in 1967, the agency is mandated by Congress through the Independent Safety Board Act of 1974 to investigate transportation accidents, determine the probable causes of the accidents, issue safety recommendations, study transportation safety issues, and evaluate the safety effectiveness of government agencies involved in transportation. The Safety Board makes public its actions and decisions through accident reports, safety studies, special investigation reports, safety recommendations, and statistical reviews. Information about available publications may be obtained by contacting: National Transportation Safety Board Public Inquiries Section, RE-51 490 L’Enfant Plaza, S.W. Washington, D.C. 20594 (202)382-6735 (800)877-6799 Safety Board publications may be purchased, by individual copy or by subscription, from: National Technical Information Service 5285 Port Royal Road Springfield, Virginia 22161 (703)487-4600 NTSB/AAR-97/05 PB97-910405 NATIONAL TRANSPORTATION SAFETY BOARD WASHINGTON, D.C. 20594 AIRCRAFT ACCIDENT REPORT UNCONTROLLED FLIGHT INTO TERRAIN ABX AIR (AIRBORNE EXPRESS) DOUGLAS DC-8-63, N827AX
    [Show full text]
  • Aircraft/Airship Data
    1 A-90 Orlyonok see SchiData.doc A-class US blimp WWI see DN-1 AASI Jetcruzer 450: 1994 certified Jetcruiser 500P: FdW 98, 7, no serial production Abbott-Baynes Scud II: glider, KOPIENORDNER ABC Robin: IM KOPIENORDNER ACAC ARJ 21-700ER: longer range -700STD ARJ 21-700STD: short range airliner, first flight scheduled late 2008, certification due late 2009, delivery due 2009, FdW 2007, 8 ARJ 21-900ER: longer range -900STD ARJ 21-900STD: longer -700 AD-1: british commercial airship 1929 ADA Aeronautical Development Agency: a division of HAL Adam Aircraft Industries A-500: 12/02 in certificationstests, type certification 5/2005, first delivery 11/05, FAA certification 9/2006, FdW 08, 12 A-700: delivery 2008, FdW 04, 12 M-309: prototype for A-500; ZEICHNUNG IN FdW 2001, 10 RA-10: IM KOPIENORDNER Ader Avion 3: trials 14.10.1897 AEG - A.E.G. - A. E. G. B.I: unarmed reconnaissance 1914 B.II: unarmed reconnaissance 1914, US-BUCH B.III: unarmed reconnaissance 1915 C.I: armed reconnaissance 1915 C.II: armed reconnaissance, in service 10/1915 C.III: prototype C. IV: armed reconnaissance 1916, IM KOPIENORDNER, US-BUCH C.IVN: night bomber C.V: prototype C.VIII: 2 built C.VIIIDr: triplane C.VIII G.I: 1915 G.IV: bomber 1916, US-BUCH G.V: 1918 J.I: ground support, KOPIENORDNER J.II: ground support 1918 Z 5: 1914, seaplane; ZEICHNUNG IN DT. LUFTFAHRT - WASSERFZ. Aeritalia see Fiat Aermacchi Aeronautica Macchi AL.60: AM.3C Bosbok: liason, observation, in service 1972, FLUGZEUGTYPEN M-311: trainer, trials 6/05, FdW 06, 14 M-346: trainer, delivery due 2009, FdW 03, 12 MB-326 Macchino: trainer, in service 2/1962; US-BUCH MB-326A: ground support, no production MB-326B: ground support, export A for Tunesia MB-326D: trainer version of A MB-326E: FLUGZEUGTYPEN MB-326F: ground support, expoert A for Ghana MB-326G: protoype MB-326GB: MB-326GC: brasilian licence built (Embraer AT-26 Xavante) MB-326H: australian ground support M.B.
    [Show full text]
  • 227A 2 2. 6.26%
    J. M. BROWNING, FIREARM, APPLICATIONFILED NOV. 26, 1913. 1,143,170. Patented June 15, 1915. 5 SHEETS-SHEET 1, NY A7/ya SSAs. 227A 2 2. 6.26% J., M., BROWNING, FIREARM, 1,148,170. Patented June 15, 1915. S N y AN N.Y. N A. E < ... I 277/255As A || A4, 4 7% (2. lug A- rary J, M, BROWN ING, FIREARM, . APPLICATION FILED NOV, 26, 1913. 1,143,170. Patented June 15, 1915. 5 SHEETS-SHEET 3. %zyszs - - ?-O-24-21 a. - /222ave & 6. J. M., BROWNING, FREARM, APPLICATION FILED Nov 26, 1913, 1,143,170. Patented June 15, 1915, 5 SHEETS-SEET 4, & | N | (S NSN. l E & HSN N s NS n N A7/ya ssas.N S J, M, BROWNING. 1,148,170. Patented June 15, 1915, /72772eys, UNITED STATES PATENT OFFICE. JoHN M, BROWNING, OF OGDEN, UTAH. FiBEARM, 1,143,170. specification of Letters Patent. Patented June 15, 1915. Application filed November 26, 1918. Serial No. 803,192. To all whom, it may concern longitudinal section, the parts within the re Be it known that I, JoHN M. BROWN fNG, ceiver being shown, however, in full. Fig. a citizen of the United States, residing at 9 is a vertical longitudinal section, the parts Ogden, Utah, have invented certain new and within the receiver being shown in section. useful Improvements in Firearms, of which Fig. 10 is a top plan of the trigger-plate and 60 the following is a specification. associated parts, removed from the gun. A principal object of this invention is to Fig.
    [Show full text]
  • NASA/FAA Tailplane Icing Program: Flight Test Report
    NASA/TP--2000-209908 DOT/FAA/AR-99/85 U.S. Department of Transportation Federal Aviation Administration NASA/FAA Tailplane Icing Program: Flight Test Report Thomas P. Ratvasky Glenn Research Center, Cleveland, Ohio Judith Foss Van Zante Dynacs Engineering Company, Inc., Brook Park, Ohio Alex Sim Dryden Flight Research Center Edwards Air Force Base, California March 2000 The NASA STI Program Office... in Profile Since its founding, NASA has been dedicated to CONFERENCE PUBLICATION. Collected the advancement of aeronautics and space papers from scientific and technical science. The NASA Scientific and Technical conferences, symposia, seminars, or other Information (STI) Program Office plays a key part meetings sponsored or cosponsored by in helping NASA maintain this important role. NASA. The NASA STI Program Office is operated by SPECIAL PUBLICATION. Scientific, Langley Research Center, the Lead Center for technical, or historical information from NASNs scientific and technical information. The NASA programs, projects, and missions, NASA STI Program Office provides access to the often concerned with subjects having NASA STI Database, the largest collection of substantial public interest. aeronautical and space science STI in the world. The Program Office is also NASA's institutional TECHNICAL TRANSLATION. English- mechanism for disseminating the results of its language translations of foreign scientific research and development activities. These results and technical material pertinent to NASA's are published by NASA in the NASA STI Report mission. Series, which includes the following report types: Specialized services that complement the STI TECHNICAL PUBLICATION. Reports of Program Office's diverse offerings include completed research or a major significant creating custom thesauri, building customized phase of research that present the results of data bases, organizing and publishing research NASA programs and include extensive data results.., even providing videos.
    [Show full text]
  • Aircraft Circulars National Advisory Coittee For
    AIRCRAFT CIRCULARS NATIONAL ADVISORY COITTEE FOR AERONAUTICS No. 141 THE C.A.M.S. 60 SEAPLANE (FRENCH) A Twin-Engine bombing and Torpedo Monoplane Washington April, 1931 NATIONAL ADVISORY COMJiI TT .E FOR AERONAUTICS AIRCRAFT CIRCULAR NO. 141 THE C.A.M.S. 60 SEAPLANE (PRENCH)* A Twin-Engine Bombing and Torpedo Monoplane The C.A.M.S. 60 (Figs. 1 : 2, 2a, and 3) which was built by the uChantiers AeroMaritimes de la Seine," and wiose.prototype, the C.A.N.S. 52, recently began its tests at Sartrouville, is a twiti-engine monoplane with a wing of medium thickness and is mounted on two floats. It is of mixed construction, much use being made of high-resistance noncorrosive steel, and is covered with fabric. Each half of the wing has a root section which supports the engine and connects the wing proper to the top longerons of the fuselage. The two root sections form a decided downward dihedral. Each half of the wing proper consists of a long rec- tangular portion of uniform section terminated by a tapering por- tion of diminishing thickness on the lower side, thus forming a slight upward Iihedral. It has two parallel box spars connected by box crosspieces, the latter being braced by rods and, in the tapered portion, by piano wires. The: trailing edge of the ta- pered portion is ailerons conjugated differentially with . largje cambered aileron covering the whole of the rectangular portion. The unbalanced stabilizing ailerons are encased a short ditandé from the wing tip.Their division *From L'Aeronautique, March, 1931, pp.
    [Show full text]
  • Les Hydravions CAMS
    LLeess hhyyddrraavviioonnss CAMS CAMS Construit à un seul exemplaire , le grand hydravion quadrimoteur CAMS 141, dernier appareil de la firme de Sartrouville, a volé de 1938 à février 1944, et accumulé 1800 heures de vol, pour la plus grande satisfaction de son équipage. LLeess hhyyddrraavviioonnss CCAAMMSS Parallèlement, Santoni entreprend en Italie la Naissance des Chantiers création d’une importante société pour fabriquer sous licence les avions d’Henry et Maurice Farman, Aéro Maritimes de la mais il y introduit aussi les produits français qu’il connaît bien : hélices Régy et Chauvière, vernis Seine Emaillite, et divers instruments de bord. Le 5 mai 1913, il crée à Varèse en Italie une société pour la Laurent-Dominique Santoni est né à Genève en construction d’hydravions, la Société anonyme de Suisse le 19 février 1877. Après des études primai- construction aéronautique Savoïa. res et secondaires en France, parlant couramment l’Italien et l’Anglais, (pour les uns il est Lawrence Santoni, pour les autres Lorenzo Santoni), il achève sa formation en décrochant un diplôme d’ingénieur. A vingt-deux ans, il suit avec passion le meeting de Reims et veut devenir aviateur. En 1910 à Port-Aviation (communes de Juvisy-sur- Orge et Viry-Châtillon) où s’ouvrent les premières écoles de l’air, il fréquente les premiers aviateurs, Louis Gaudart, chef pilote Voisin, le comte de Saint-Germain, chef pilote de l’école Donnet sur FBA type C aux couleurs de la marine italienne (1915). Le type C italien construit chez S.I.A.I.-Savoïa était propulsé par un moteur fixe appareil Blériot, Pauwels et Bobba, les pilotes de à six cylindres en ligne Isotta-Fraschini de 120 ch.
    [Show full text]