NEWSLETTER Book for Guest’S Lunch on 21 May
Total Page:16
File Type:pdf, Size:1020Kb
Load more
Recommended publications
-
1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27
A B C D E F 1 A012 A03009 125 DOMINIE 1.72 AIRCRAFT 2 A009 A05871 1804 STEAM LOCO 1.32 STEAM ENGINE 3 A013 A02447 1905 ROLLS ROYCE 1.32 CAR 4 A002 A02444 1911 ROLLS ROYCE 1.32 CAR 5 A002 A02443 1912 MODEL T FORD 1.32 CAR 6 A002 A02450 1926 MORRIS COWLEY 1.32 CAR 7 A002 A02446 1930 BENTLEY 1.32 CAR 8 ROB A20440 1930 BENTLEY 1.12 CAR 9 A028 A08440 1932 CHRYSLER IMPERIAL 1.25 CAR 10 A002 A02441 1933 ALFA ROMEO 1.32 CAR 11 A002 A01305 25PDR FIELD GUN & MORRIS QUAD 1.76 VEHICLE 12 ROB A02552 2ND DRAGOON 1815 54MM FIGURE 13 ROB 50 YEARS OF THE GREATEST PLASTIC KITS BOOK 14 A013 A02303 88MM GUN & TRACTOR 1.76 VEHICLE 15 ROB A02303 88MM GUN & TRACTOR (D-DAY) 1.76 VEHICLE 16 A026 A06012 A-10 THUNDERBOLT II 1.72 AIRCRAFT 17 ROB ITALERI 097 A-10 WARTHOG 1.72 AIRCRAFT 18 A026 REVELL 04206 A300-600 ST BELUGA 1144 AIRCRAFT 19 A008 A01028 A6M2 ZERO (VJ DAY) 1.72 AIRCRAFT 20 ROB A50127 A6M2B -21 (2011) 1.72 AIRCRAFT PAINTS IN BOX 21 ROB A01005 A6M2B ZERO 1.72 AIRCRAFT 22 A031 REVELL 4366 A-7A CORSAIR 1.72 AIRCRAFT 23 A007 A04211 ADMIRAL GRAF SPEE 1600 SHIP 24 ROB A01314 AEC MATADOR (D-DAY) 1.76 VEHICLE 25 A026 A04046 AH-1 T SEA COBRA 1.72 HELICOPTER 26 A005 A03077 AH-64 APACHE LONGBOW 1.72 HELICOPTER 27 A014 A07101 AH-64 APACHE LONGBOW 1.48 HELICOPTER 28 A026 A04044 AH-64 APACHE LONGBOW 1.72 HELICOPTER 29 A008 A02014 AICHI D3AI VAL (VJ DAY) 1.72 AIRCRAFT 30 ROB AIRFIX 1972 CATALOUGE BOOK 31 ROB AIRFIX 1974 CATALOUGE BOOK 32 ROB AIRFIX 1983 CATALOUGE BOOK 33 ROB A78183 AIRFIX 2007 CATALOUGE BOOK 34 ROB A78184 AIRFIX 2008 CATALOUGE BOOK 35 ROB AIRFIX CLUB -
Over Thirty Years After the Wright Brothers
ver thirty years after the Wright Brothers absolutely right in terms of a so-called “pure” helicop- attained powered, heavier-than-air, fixed-wing ter. However, the quest for speed in rotary-wing flight Oflight in the United States, Germany astounded drove designers to consider another option: the com- the world in 1936 with demonstrations of the vertical pound helicopter. flight capabilities of the side-by-side rotor Focke Fw 61, The definition of a “compound helicopter” is open to which eclipsed all previous attempts at controlled verti- debate (see sidebar). Although many contend that aug- cal flight. However, even its overall performance was mented forward propulsion is all that is necessary to modest, particularly with regards to forward speed. Even place a helicopter in the “compound” category, others after Igor Sikorsky perfected the now-classic configura- insist that it need only possess some form of augment- tion of a large single main rotor and a smaller anti- ed lift, or that it must have both. Focusing on what torque tail rotor a few years later, speed was still limited could be called “propulsive compounds,” the following in comparison to that of the helicopter’s fixed-wing pages provide a broad overview of the different helicop- brethren. Although Sikorsky’s basic design withstood ters that have been flown over the years with some sort the test of time and became the dominant helicopter of auxiliary propulsion unit: one or more propellers or configuration worldwide (approximately 95% today), jet engines. This survey also gives a brief look at the all helicopters currently in service suffer from one pri- ways in which different manufacturers have chosen to mary limitation: the inability to achieve forward speeds approach the problem of increased forward speed while much greater than 200 kt (230 mph). -
The Fairey Rotodyne
THE FAIREY ROTODYNE The Rotodyne represents an entirely new approach to air transport, and its amazing performance is a triumph for the British Au.i4.ii Industry. It is the first true vertical take-off airliner, and is capable of carrying a full load of passengers or freight, operating from airlicUU no larger than two tennis courts. Unlike the conventional helicopter the Rotodyne is economical to operate, and also capable of much hijr.lin speeds and greater range. The prototype Rotodyne, built under a Ministry of Supply contract, first flew on 6th November, 1957, and achieved its first transition to complete autorotative flight in April, 1958. This prototype, the subject of this model, is capable of carrying 48 passengers or five tun» of freight; the eventual production version will be larger, carrying up to 70 passengers or 8 tons of freight, and will be powered by the more powerful Rolls-Royce Tyne engines in place of the present Elands. A striking demonstration of the Rotodyne's performance was given in January, 1959, when it set up a record 191 m.p.h. on a 100 kin closed circuit. This exceeds the previous record by 49 m.p.h.j and is even 29 m.p.h. faster than the previous absolute speed record for heli- copters. This speed, together with the range of 450 miles, to be increased to 650 miles in the developed version, and of course the weighi lifting and vertical take-off performance, puts the Fairey Rotodyne into a class of its own. Already three airline operators have indicated their intention of buying the Rotodyne, and great interest is being shown by civilian and military operators throughout Europe and America. -
Thrust Control of Vtol Aircraft – Part Deux Daniel C. Dugan
THRUST CONTROL OF VTOL AIRCRAFT – PART DEUX DANIEL C. DUGAN [email protected] Aero Engineer/Research Pilot´‡ NASA Ames Research Center Moffett Field, California ABSTRACT Thrust control of Vertical Takeoff and Landing (VTOL) aircraft has always been a debatable issue. In most cases, it comes down to the fundamental question of throttle versus collective. Some aircraft used throttle(s), with a fore and aft longitudinal motion, some had collectives, some have used Thrust Levers where the protocol is still “Up is Up and Down is Down,” and some have incorporated both throttles and collectives when designers did not want to deal with the Human Factors issues. There have even been combinations of throttles that incorporated an arc that have been met with varying degrees of success. A previous review was made of nineteen designs without attempting to judge the merits of the controller. Included in this paper are twelve designs entered in competition for the 1961 Tri-Service VTOL transport. Entries were from a Bell/Lockheed tiltduct, a North American tiltwing, a Vanguard liftfan, and even a Sikorsky tiltwing. Additional designs were submitted from Boeing Wichita (direct lift), Ling-Temco-Vought with its XC-142 tiltwing, Boeing Vertol’s tiltwing, Mcdonnell’s compound and tiltwing, and the Douglas turboduct and turboprop designs. A private party submitted a re-design of the Breguet 941 as a VTOL transport. It is important to document these 53 year-old designs to preserve a part of this country’s aviation heritage. INTRODUCTION During the design phase of an aircraft, the control of Vertical Takeoff and Landing (VTOL) aircraft, thrust should be a straightforward process. -
(12) United States Patent (10) Patent No.: US 8,991,744 B1 Khan (45) Date of Patent: Mar
USOO899.174.4B1 (12) United States Patent (10) Patent No.: US 8,991,744 B1 Khan (45) Date of Patent: Mar. 31, 2015 (54) ROTOR-MAST-TILTINGAPPARATUS AND 4,099,671 A 7, 1978 Leibach METHOD FOR OPTIMIZED CROSSING OF 35856 A : 3. Wi NATURAL FREQUENCIES 5,850,6154. W-1 A 12/1998 OSderSO ea. 6,099.254. A * 8/2000 Blaas et al. ................... 416,114 (75) Inventor: Jehan Zeb Khan, Savoy, IL (US) 6,231,005 B1* 5/2001 Costes ....................... 244f1725 6,280,141 B1 8/2001 Rampal et al. (73) Assignee: Groen Brothers Aviation, Inc., Salt 6,352,220 B1 3/2002 Banks et al. Lake City, UT (US) 6,885,917 B2 4/2005 Osder et al. s 7,137,591 B2 11/2006 Carter et al. (*) Notice: Subject to any disclaimer, the term of this 16. R 1239 sign patent is extended or adjusted under 35 2004/0232280 A1* 11/2004 Carter et al. ............... 244f1725 U.S.C. 154(b) by 494 days. OTHER PUBLICATIONS (21) Appl. No.: 13/373,412 John Ballard etal. An Investigation of a Stoppable Helicopter Rotor (22) Filed: Nov. 14, 2011 with Circulation Control NASA, Aug. 1980. Related U.S. Application Data (Continued) (60) Provisional application No. 61/575,196, filed on Aug. hR". application No. 61/575,204, Primary Examiner — Joseph W. Sanderson • Y-s (74) Attorney, Agent, or Firm — Pate Baird, PLLC (51) Int. Cl. B64C 27/52 (2006.01) B64C 27/02 (2006.01) (57) ABSTRACT ;Sp 1% 3:08: A method and apparatus for optimized crossing of natural (52) U.S. -
A Review and Statistical Modelling of Accidental Aircraft Crashes Within Great Britain MSU/2014/07
Harpur Hill, Buxton Derbyshire, SK17 9JN T: +44 (0)1298 218000 F: +44 (0)1298 218590 W: www.hsl.gov.uk Loughborough University Loughborough Leicestershire LE11 3TU UK P: +44 (0)1509 223416 F: +44 (0)1509 223981 http://www.lboro.ac.uk/transport 12.09.2014 A Review and Statistical Modelling of Accidental Aircraft Crashes within Great Britain MSU/2014/07 HSL Report Content Loughborough University Report Content Report Approved Report Approved Andrew Curran David Pitfield for Issue By: for Issue By: Date of Issue: 12/09/2014 Date of Issue: 12/09/2014 Lead Author: Emma Tan Lead Author: David Gleave Contributing Contributing Nick Warren David Pitfield Author(s): Author(s): Technical Technical David Pitfield / Nick Warren Reviewer(s): Reviewer(s): David Gleave David Pitfield / Editorial Reviewer: Charles Oakley Editorial Reviewer: David Gleave HSL Project Loughborough PH06315 N/A Number: Project Number: HSL authored 7 ,8 ,9 Appendix (a) Loughborough 3 ,4 ,5 ,6 ,10 ,12 sections and Appendix (b) authored sections Appendix (c ) HSL/Loughborough HSL/Loughborough 1, 2, 11 1, 2, 11 Joint authorship Joint authorship 1, 2 ,7 ,8 ,9 ,11 , Loughborough HSL Quality 3 ,4 ,5 ,6 ,10 ,12 Appendix (a) and quality approved approved sections Appendix (c ) Appendix (b) sections DISTRIBUTION Matthew Lloyd-Davies Technical Customer Tim Allmark Project Officer Gary Dobbin HSL Project Manager Andrew Curran Science and Delivery Director Charles Oakley Mathematical Sciences Unit Head David Pitfield Loughborough University David Gleave Loughborough University © Crown copyright (2014) EXECUTIVE SUMMARY Background One of the hazards associated with nuclear facilities in the United Kingdom is accidental impact of aircraft onto the sites. -
April 2020 the Current Exemption That Allows GA Pilots to Self- PRINTING Declare Their Medical Fitness Expires
The official magazine of the Aircraft Owner and Pilots Association www.aopa.co.uk turbopropThe with The TBM 940 has the most advanced cockpit in a turobprop – big-jet Tom Horne takes one for a flight dreams REVALIDATION COURSE FLIGHT DIRECTORY TECH AND BOOKS Matt Lane explains exactly All new 2020 FLIGHT The latest General Aviation what happens at the two-day DIRECTORY! Special products and books that AOPA seminars pullout section are on sale now MAGAZINE 04.2019 FREE TO MEMBERS WWW.AOPA.CO.UK 03 CHAIRMAN'S MESSAGE A CHANGING EDITOR David Rawlings NEW WORLD [email protected] HAT DOES the UK leaving EASA mean for AOPA members? EASA's powers will revert to the CAA at the end of 2020, and there will be no ART EDITOR Dan Payne amendments to UK legislation in the short term. However, from 1 January [email protected] W 2021 there will be no more EASA licences issued by the CAA. There has already been significant action by Flight Training Organisations to move their SUB EDITOR operations to other European states, the Netherlands and Ireland being favourites, Lucy Debenham so the issue of EASA licences for their students moving up the aviation career ladder is uninterrupted. Currently the cost of the skills test for a CPL (IR) in the CONTRIBUTORS UK is about £800 compared with much lower fees in other parts of Europe, and Pauline Vahey, John Walker, I understand, about €65 in France for a similar test. The consequence of this lack Matt Lane, David Chambers, of activity by the CAA will be a reduction of income for it. -
L4582 London
London CTR Reclassification Consultation Document Version 1.0 26 September 2013 Prepared by Bradley Taylor Airspace Assurance 2 London CTR Reclassification: Consultation Document London CTR Reclassification - Consultation Document Prepared by: Bradley Taylor Airspace Assurance Version 1.0 26 September 2013 London CTR Reclassification: Consultation Document 3 Table of contents Executive Summary 5 Section 1: Document Structure 6 1.1 Section Summary 6 Section 2: Introduction 7 2.1 Why the Need for Change? 7 2.2 Assumptions 7 2.3 Audience 8 Section 3: The Consultation 9 3.1 Purpose of the Consultation 9 3.2 Scope of the Consultation 9 3.3 Development Objectives 10 3.4 Pre-Consultation 11 3.5 Consultation and Implementation Time Line 12 Section 4: Current Operations 13 4.1 Description of the Airspace 13 4.2 Air Traffic Operations 18 4.3 SERA Implementation within the London CTR 20 Section 5: Option Assessment 21 5.1 Consideration of Possible Options 21 5.2 Summary of the Preferred (Class D) Option 26 5.3 What to do next? 26 Section 6: Next Steps 27 6.1 How Do I Respond? 27 Section 7: Airspace Classification Options in Detail 31 7.1 Class C Option (discounted) 31 7.2 Class D Option (NATS preferred) 39 Section 8: References 50 Section 9: Glossary 51 Section 10: Appendices 53 Appendix A: List of Consultees 53 Appendix B: Class B Option (discounted) 57 Appendix C: Cabinet Office Code of Practice on Consultation 59 4 London CTR Reclassification: Consultation Document The UK adoption of the Standardised European Rules of the Air (SERA) is driving a change in UK aviation law. -
Aerodynamic Concept of the Uav in the Gyrodyne Configuration
TRANSACTIONS OF THE INSTITUTE OF AVIATION 1 (250) 2018, pp. 49–66 DOI: 10.2478/tar-2018-0005 © Copyright by Wydawnictwa Naukowe Instytutu Lotnictwa AERODYNAMIC CONCEPT OF THE UAV IN THE GYRODYNE CONFIGURATION Jan Muchowski*, Marek Szumski*, Andrzej Krzysiak** *Department of Fluid Mechanics and Aerodynamics, Mechanical Engineering and Aeronautics, Rzeszow University of Technology, al. Powstańców Warszawy 8, 35-959 Rzeszow **Aerodynamics Department, Institute of Aviation, Al. Krakowska 110/114, 02-256 Warsaw [email protected], [email protected], [email protected], Abstract The article presents an aerodynamic concept of UAV in the gyrodyne configuration, as a more efficient one than the currently used UAV airframe configuration applied for monitoring tasks of pow- er lines and railway infrastructure. A sample task which is realised by conceptual gyrodyne based on monitoring aerial power lines was characterised and described . The assumed idea of UAV was shown in comparison to the currently used aircraft configuration presented in the introduction. Referring to momentum theory, hover efficiency of the multicopter and the helicopter was evaluated. In relation to the helicopter, an initial draft of the airframe conception accompanied by a description of advan- tages of the gyrodyne configuration was exposed. Problems related to the gyrodyne configuration were emphasised in the summary. Keywords: aerodynamic concept, UAV, VTOL, gyrodyne, airframe configuration 1. INTRODUCTION In recent years a dynamic growth of the UAV (Unmanned Aerial Vehicle) usage in civil and mili- tary missions can be observed . Economic aspects are the main reasons of that increase, i.e. the purchas- ing cost of the UAS (Unmanned Aircraft System) varies from 40% up to 80% of the manned system cost. -
Performance Analysis of the Slowed-Rotor Compound Helicopter Configuration
Performance Analysis of the Slowed-Rotor Compound Helicopter Configuration Matthew W. Floros Wayne Johnson Raytheon ITSS Army/NASA Rotorcraft Division Moffett Field, California NASA Ames Research Center Moffett Field, California The calculated performance of a slowed-rotor compound aircraft, particularly at high flight speeds, is exam- ined. Correlation of calculated and measured performance is presented for a NASA Langley high advance ratio test and the McDonnell XV-1 demonstrator to establish the capability to model rotors in such flight conditions. The predicted performance of a slowed-rotor vehicle model based on the CarterCopter Technology Demonstra- tor is examined in detail. An isolated rotor model and a model of a rotor and wing are considered. Three tip speeds and a range of collective pitch settings are investigated. A tip Mach number of 0.2 and zero collective pitch are found to be the optimum condition to minimize rotor drag. Performance is examined for both sea level and cruise altitude conditions. Nomenclature Much work has been focused on tilt rotor aircraft; both military and civilian tilt rotors are currently in development. But other configurations may provide comparable benefits to CT thrust coefficient tilt rotors in terms of range and speed. Two such configura- CQ torque coefficient tions are the compound helicopter and the autogyro. These CH longitudinal inplane force coefficient configurations provide STOL or VTOL capability, but are ca- D drag pable of higher speeds than a conventional helicopter because L lift the rotor does not provide the propulsive force or at high MTIP tip Mach number speed, the vehicle lift. The drawback is that redundant lift VT tip speed and/or propulsion add weight and drag which must be com- q dynamic pressure pensated for in some other way. -
Download (6MB)
Trchalik, Josef (2009) Aeroelastic modelling of gyroplane rotors. PhD thesis. http://theses.gla.ac.uk/1232/ Copyright and moral rights for this thesis are retained by the author A copy can be downloaded for personal non-commercial research or study, without prior permission or charge This thesis cannot be reproduced or quoted extensively from without first obtaining permission in writing from the Author The content must not be changed in any way or sold commercially in any format or medium without the formal permission of the Author When referring to this work, full bibliographic details including the author, title, awarding institution and date of the thesis must be given Glasgow Theses Service http://theses.gla.ac.uk/ [email protected] Aeroelastic Modelling of Gyroplane Rotors Josef Trchalík, Dipl.Ing. Ph. D. Thesis Department of Aerospace Engineering University of Glasgow July 2009 Thesis submitted to the Faculty of Engineering in fulfillment of the requirements for the degree of Doctor of Philosophy c J. Trchalík, 2009 Abstract The gyroplane represents the first successful rotorcraft design and it paved the way for the development of the helicopter during the 1940s. Gyroplane rotors are not powered in flight and work in autorotative regime and hence the characteristics of a helicopter rotor during powered flight and a rotor in autorotation differ sig- nificantly. Gyroplanes in the UK have been involved in number of fatal accidents during the last two decades. Despite several research projects focused on gyroplane flight dynamics, the cause of some of gyroplane accidents still remains unclear. The aeroelastic behaviour of autorotating rotors is a relatively unexplored problem and it has not yet been investigated as possible cause of the accidents. -
Where to Fly Guide & Corporate Member Listing
AOPAAOPA WHERE TO FLY GUIDE & CORPORATE MEMBER LISTING The Pilot Centre Cambridge Flying Group Lands End Aero Club Denham Aerodrome Cambridge (Westward Airways) Denham Marshall’s Airport Lands End Aerodrome Uxbridge Newmarket Road St Just Middlesex UB9 5DF Cambridge CB5 8RX Penzance Tel: 01895 833838 Tel: 01223 293343 Cornwall TR19 7RL Fax: 01895 832267 Fax: 01223 294147 Tel: 01736 788771 Email: [email protected] Email: Fax: 01747 787651 BEDFORDSHIRE Website: www.egld.com/tpc [email protected] Email: flyingclub@islesofscilly- Bedfordshire School of Flying Website: travel.co.uk Piper Warrior 3 [email protected] Web:www.landsendairportco.uk Cranfield Airfield Cessna 152 5 Cranfield Cessna 172 1 Tiger Moth 2 Cessna 152 1 Bedfordshire MK43 0AL Cessna 182 1 Fuji RA200-180 1 Tel: 01234 752817 Cessna 152 Aerobat 1 Bellanca Citabria 1 Cessna 172 1 Fax: 01234 752809 NSF Sibson Email: [email protected] Wycombe Air Centre Ltd Sibson Aerodrome Website: www.cabairflyingschools.com Wycombe Air Park Wansford CUMBRIA Booker Peterborough Carlisle Flight Training Limited Grumman Cheetah 4 Marlow PE8 6NE Carlisle Airport Grumman Tiger 3 Buckinghamshire SL7 3DR Tel: 01832 280289 Grumman Cougar 1 Carlisle Tel: 01494 443737 Fax: 01832 280675 Cumbria CA6 4NW Piper Arrow 1 Fax: 01494 465456 Email: [email protected] Robinson R22 2 Tel: 01228 573344 / 07834 559560 Email: [email protected] Website: www.nsof.co.uk Email:[email protected] Website: wycombeaircentre.co.uk Cabair College of Training Robin