Recreational Flyer January - February 2010 Elevated: Angus Watt’S Ch-750
Total Page:16
File Type:pdf, Size:1020Kb
Load more
Recommended publications
-
Application to the Flight
Journal name 000(00):1–13 A Methodology for Vehicle and Mission ©The Author(s) 2010 Reprints and permission: Level Comparison of More Electric sagepub.co.uk/journalsPermissions.nav DOI:doi number Aircraft Subsystem Solutions - Application http://mms.sagepub.com to the Flight Control Actuation System Imon Chakraborty∗ and Dimitri N. Mavris† Aerospace Systems Design Laboratory, Georgia Institute of Technology, Atlanta, GA 30332, USA Mathias Emeneth‡ and Alexander Schneegans§ PACE America Inc., Seattle, WA 98115, USA Abstract As part of the More Electric Initiative, there is a significant interest in designing energy-optimized More Electric Aircraft, where electric power meets all non-propulsive power requirements. To achieve this goal, the aircraft subsystems must be analyzed much earlier than in the traditional design process. This means that the designer must be able to compare competing subsystem solutions with only limited knowledge regarding aircraft geometry and other design characteristics. The methodology presented in this work allows such tradeoffs to be performed, and is driven by subsystem requirements definition, component modeling and simulation, identification of critical or constraining flight conditions, and evaluation of competing architectures at the vehicle and mission level. The methodology is applied to the flight control actuation system, where electric control surface actuators are likely to replace conventional centralized hydraulics in future More Electric Aircraft. While the potential benefits of electric actuation are generally accepted, there is considerable debate regarding the most suitable electric actuator - electrohydrostatic or electromechanical. These two actuator types form the basis of the competing solutions analyzed in this work, which focuses on a small narrowbody aircraft such as the Boeing 737-800. -
WINGS of SILVER PIPER J-3 Cub OPERATIONS MANUAL &
WINGS OF SILVER PIPER J-3 Cub OPERATIONS MANUAL & POH (this Manual and POH is not intended for flight and is intended only for flight simulation use) Written by Mitchell Glicksman, © 2009 i Table of Contents Introduction..............................................................................................................................................................................................................1 The 747 Captain Who Forgot How to Fly................................................................................................................................................................8 A Short History of a Small Airplane......................................................................................................................................................................13 Quick Start Guide...................................................................................................................................................................................................18 System Requirements........................................................................................................................................................................................18 Installation.........................................................................................................................................................................................................20 Settings..............................................................................................................................................................................................................20 -
ARTICLE 5 Assigned-Space Aircraft Parking
ARTICLE 5 Assigned-Space Aircraft Parking Section 500. Assigned-space aircraft parking designation. 510. Assigned-space use and fees. 520. Assigned-space permit application. 530. Assigned-space permit. 540. Cancellation of an assigned-space permit. 550. Assigned-space permit lottery. 560. Assigned-space switch list. 570. Assigned-space wait list. 580. Birchwood airport transitional compliance requirements. 590. Definitions. 17 AAC 45.500. Assigned-space aircraft parking designation. (a) The commissioner will designate an airport for assigned-space aircraft parking if the commissioner determines in writing that the designation is in the best interest of the state. In making this determination, the commissioner will consider the applicable factors set out at 17 AAC 45.900 and the following: (1) the number of aircraft based at the airport, other than those based on leased premises, the demand for transient aircraft fee parking, and the amount of space available for assigned-space aircraft parking at the airport; (2) the potential impact of assigned-space aircraft parking fees on airport users; and (3) the department's estimate of the cost to implement the requirements of 17 AAC 45.500 - 17 AAC 45.590 at the airport compared to the potential revenue the department would receive for assigned-space aircraft parking at the airport. (b) The department will inform the public that the commissioner has designated an airport for assigned-space aircraft parking by giving notice in accordance with 17 AAC 45.400. The notice will include (1) the name -
Setting up Ailerons and Flaperons on a DLG (Discus Launch Glider) by Andy Kunz
Setting up Ailerons and Flaperons on a DLG (Discus Launch Glider) by Andy Kunz Originally Posted by kgantz: While waiting for parts to be delivered I am still reading a lot about how to initially set up ailerons / flaperons. One of the best descriptions I've found is this post in the DLG forum. After reading this post, I understand that flaperon trim and aileron trim are handled separately by the radio. This is not obvious to people who have not done this before but, I guess because you are working with 1 moving surface but it has 2 jobs, trimming has to work a little differently for each job! So now my question is, on the Spektrum radios-- DX 9 in my case, is the aileron portion of the adjustment done with Dual Rates as suggested by the poster or is there a different way. Reply by AndyKunz: The logic is that one is a roll trim, the other is a camber trim. You'll find that we're pretty consistent with that sort of thing throughout the radio. Use the Dual Rates to adjust travel based on a switch, for instance in launch mode vs. thermal mode vs. landing mode. If it doesn't need to change based on a switch, do it with Servo Travel instead of Dual Rates. If you are working on a V-Tail or Elevon model, then you would use Dual Rates to adjust the ratio between pitch and roll/yaw. Use Servo Travel to adjust the maximum amount in the highest position of the Dual Rates switch. -
Garmin Reveals Autoland Feature Rotorcraft Industry Slams Possible by Matt Thurber NYC Helo Ban Page 45
PUBLICATIONS Vol.50 | No.12 $9.00 DECEMBER 2019 | ainonline.com Flying Short-field landings in the Falcon 8X page 24 Regulations UK Labour calls for bizjet ban page 14 Industry Forecast sees deliveries rise in 2020 page 36 Gratitude for Service Honor flight brings vets to D.C. page 41 Air Transport Lion Air report cites multiple failures page 51 Rotorcraft Garmin reveals Autoland feature Industry slams possible by Matt Thurber NYC helo ban page 45 For the past eight years, Garmin has secretly Mode. The Autoland system is designed to Autoland and how it works, I visited been working on a fascinating new capabil- safely fly an airplane from cruising altitude Garmin’s Olathe, Kansas, headquarters for ity, an autoland function that can rescue an to a suitable runway, then land the airplane, a briefing and demo flight in the M600 with airplane with an incapacitated pilot or save apply brakes, and stop the engine. Autoland flight test pilot and engineer Eric Sargent. a pilot when weather conditions present can even switch on anti-/deicing systems if The project began in 2011 with a Garmin no other safe option. Autoland should soon necessary. engineer testing some algorithms that could receive its first FAA approval, with certifi- Autoland is available for aircraft manu- make an autolanding possible, and in 2014 cation expected shortly in the Piper M600, facturers to incorporate in their airplanes Garmin accomplished a first autolanding in followed by the Cirrus Vision Jet. equipped with Garmin G3000 avionics and a Columbia 400 piston single. In September The Garmin Autoland system is part of autothrottle. -
An Investigation of the Effects of Flaperon Actuator Failure on Flight Maneuvers of a Supersonic Aircraft
Research Paper ISSN 2383-4986 International Journal of Aerospace System Engineering http://dx.doi.org/10.20910/IJASE.2016.3.2.1 Vo l . 3, No.2, pp.1-8 (2016) An Investigation of the Effects of Flaperon Actuator Failure on Flight Maneuvers of a Supersonic Aircraft Seyool Oh1†, Inje Cho1, Craig McLaughlin2 1Aircraft Research & Development Division, Korea Aerospace Industries, ltd, KOREA 2Dept. of Aerospace Engineering, The University of Kansas U.S.A. †E-mail:[email protected] Abstract The improvements in high performance and agility of modern fighter aircraft have led to improvements in survivability as well. Related to these performance increases are rapid response and adequate deflection of the control surfaces. Most control surface failures result from the failure of the actuator. Therefore, the failure and behavior of the actuators are essential to both combat aircraft survivability and maneuverability. In this study, we investigate the effects of flaperon actuator failure on flight maneuvers of a supersonic aircraft. The flight maneuvers were analyzed using six degrees of freedom (6DOF) simulations. This research will contribute to improvements in the reconfiguration of control surfaces and control allocation in flight control algorithms. This paper compares the results of these 6DOF simulations with the horizontal tail actuator failures analyzed previously. Key Words : Flaperon, Actuator failure, Flight maneuver, Supersonic aircraft , Combat aircraft only for specific flight phases. Primary control 1. Introduction surfaces are generally built into the aircraft wings In the past, combat aircraft were designed using the and empennage. Typical primary controls include concept of static stability for safety. However, as the elevators on the horizontal tail, rudder on the technologies of aircraft developed and the vertical tail, and ailerons on the wings [3]. -
10CAG/10CHG/10CG-2.4Ghz 10-CHANNEL RADIO CONTROL SYSTEM
10CAG/10CHG/10CG-2.4GHz 10-CHANNEL RADIO CONTROL SYSTEM INSTRUCTION MANUAL Technical updates and additional programming examples available at: http://www.futaba-rc.com/faq Entire Contents ©Copyright 2009 1M23N21007 TABLE OF CONTENTS INTRODUCTION ........................................................... 3 Curve, Prog. mixes 5-8 ............................................. 71 Additional Technical Help, Support and Service ........ 3 GYA gyro mixing (GYRO SENSE) ............................... 73 $SSOLFDWLRQ([SRUWDQG0RGL¿FDWLRQ ........................ 4 Other Equipment ....................................................... 74 Meaning of Special Markings ..................................... 5 Safety Precautions (do not operate without reading) .. 5 Introduction to the 10CG ............................................ 7 GLIDER (GLID(1A+1F)(2A+1F)(2A+2F)) FUNCTIONS . 75 &RQWHQWVDQG7HFKQLFDO6SHFL¿FDWLRQV........................ 9 Table of contents........................................................ 75 Accessories ............................................................... 10 Getting Started with a Basic 4-CH Glider ................ 76 Transmitter Controls & GLIDER-SPECIFIC BASIC MENU FUNCTIONS ........ 78 6ZLWFK,GHQWL¿FDWLRQ$VVLJQPHQWV ............................. 11 Model type (PARAMETER submenu) ........................... 78 Charging the Ni-Cd Batteries ................................... 15 MOTOR CUT ................................................................ 79 Stick Adjustments .................................................... -
DESIGN and ANALYSIS of PERFORMANCE PARAMETERS of WING with FLAPERONS Debanjali Dey, R.Aasha #Department of Aeronautical Engineering , KCG College of Technology
International Journal of Scientific Research and Review ISSN NO: 2279-543X DESIGN AND ANALYSIS OF PERFORMANCE PARAMETERS OF WING WITH FLAPERONS Debanjali Dey, R.Aasha #Department of Aeronautical Engineering , KCG College Of Technology. 1. [email protected] 2. [email protected] ABSTRACT- The main objective of this project is to design a flaperon for a wing and compare the performance characteristic of this flaperon-wing combination with that of conventional wing design that makes use of separate flap and aileron. Theoretical analysis and comparison is performed following which the computational analysis is carried out to validate the results. Further aim is to give a clarity on the fact that the use of this high lift device aids in improvising the aerodynamic characteristics of a wing by experimental testing of the wing design incorporated with flaperon, which is designed using a special methodology. Then, modification of wing design can be done to overcome the drawbacks of flaperons if any. INTRODUCTION - When looking at an aircraft, it is easy to observe that they have a number of common features: wings, a tail with vertical and horizontal wing sections, engines to propel them through the air, and a fuselage to carry passengers or cargo. If, however, you take a more critical look beyond the gross features, you also can see subtle, and sometimes not so subtle, differences. The reasons for these differences, why the designers configured them this way, is quite an intriguing study. Today, 100,000 flights will safely crisscross the planet. At no time in history have our lives been so global and full of possibility. -
Designing and Development of Unmanned Aerial Vehicle
ICAS 2002 CONGRESS DESIGNING AND DEVELOPMENT OF UNMANNED AERIAL VEHICLE MUHAMMAD ASIM Engineering Wing PAF Base Minhas PAKISTAN,43175 [email protected] DR ABID ALI KHAN Aerospace Engg Dept College of Aeronautical Engg Risalpur,24090 National University of Science and Technology [email protected] Keywords: UAV-Ip Abstract in direct combat. Even current high-tech UAV’s such as the Darkstar are limited to non- With the advancement in science and combative missions. In an age when the technology, the aviation industry is increasingly physiological tolerances and physical concentrating on the development of Remotely capabilities of the crew restrain the limits of Piloted Vehicles (RPVs), Unmanned Aerial performance of a modern fighter, the use of a Vehicles (UAVs) and Unmanned Combat Aerial UAV in a combat role deserves some Vehicles (UCAVs). The Unmanned Aerial consideration. Vehicle (UAV) are being used for many years for a variety of different tasks like reconnaissance, bomb damage assessment 2.0 Design Philosophy and Goals (BDA), scientific research, escort EW, decoying guiding SAMs and AAMs, and target practice. The principle goal in the UAV-Ip (Unmanned These UAVs will replace the conventional Aerial Vehicle - Interceptor) design process was aircraft in several roles and even perform novel to create an interceptor, which could super assignments. The hostile battlefield cruise to intercept a target in a minimal time at a environments and difficult access areas can be maximum possible range. The application of monitored without endangering human life. This this aircraft would be defensive in nature, when paper elaborate the designing of UAV that can conventional aircraft are immediately be used as interceptor and can perform unavailable or unable to deploy. -
KOKU-KAN-SANJI-504 Date: 09/18/20 No: KOKU-KAN-SANJI-449 Date: 08/17/21 No: KOKU-KAN-SANJI-276
(Unofficial Translation) Date: 09/27/18 No: KOKU-KAN-SANJI-614 Date: 08/23/19 No: KOKU-KAN-SANJI-504 Date: 09/18/20 No: KOKU-KAN-SANJI-449 Date: 08/17/21 No: KOKU-KAN-SANJI-276 Director of Air Transport Safety Unit Aviation Safety and Security Department Civil Aviation Bureau of Japan Ministry of Land, Infrastructure, Transport and Tourism Subject: The Detailed Regulations of the Technical Standard to Prevent Objects Falling off Airplanes 1. Purpose. Based on the provisions of the Technical Standard to Prevent Objects Falling off Airplanes (hereinafter referred to as “the Standard”) and in order to bring it into effect, the Detailed Regulations of the Technical Standard to Prevent Objects Falling off Airplanes (hereinafter referred to as “the Detailed Regulations”) is established as follows. 2. Applicability. The applicability of the Detailed Regulations is the same as the Standard. 3. Application for Licenses or Authorization. The application under the provisions of the Standard shall meet the following requirements. However, the operation manual or the maintenance manual of domestic air carriers may contain the following matters in lieu of the application matters. 3-1 Engineering management. 3-1-1 The operators must have a system to collect the information of falling objects, analyze and assess from the engineering aspect, and based on these results, develop countermeasures (inspection, maintenance and others) and implement them under 3-1 of the Standard. 3-1-2 The operators must nominate a person who is to be the supervisor of the system as referred to in the preceding paragraph, and take corrective actions properly under the supervision of the person. -
DART Brochure
DART SERIES THE NEXT LEVEL OF VERSATILITY FROM CONCEPT TO PRESENT general information The all-carbon-fiber DART Series, envisioned as an aerobatic (+7/- MAIDEN FLIGHT DART-450 4G) tandem trainer, features centre stick control, ejection seats, a 17 MAY 2016 five-blade MT propeller and a Garmin avionics system. ENGINE VARIANTS ▪ Turboprop engine AI-450 CP (450 SHP) manufactured by Motor Sich for DART-450 ▪ Turboprop engine GE H75-A (550 SHP) manufactured by General Electric for DART-550 KINDS OF OPERATION ▪ VFR (day and night) and IFR ▪ Take-off and landing on paved surfaces or grass surfaces APPLICATIONS Basic to advanced flight training, Aerobatic, Formation, Multi Role STRUCTURE All composite aircraft CFRP (Carbon Fiber Reinforced Polymer). MOCK UP DART-450 From the very beginning, DEC 2015 CERTIFICATION STANDARD Diamond Aircraft knew that the DART series will be something CS/FAR23 1) unmatched on the market and will eliminate old generation CATEGORY trainer from the market for a Aerobatic / Utility (Multi Role) very long period of time. KICK OFF DART-450 ROLL OUT DART-450 MAIDEN FLIGHT DART-550 MAY 2015 APRIL 2016 03 MAY 2018 1) Certification ongoing Page 3 DART FEATURES TANDEM SEAT, CENTRE STICK CONTROL, EJECTION SEATS, TOUCH SCREEN AVIONICS dart FEATURES HOTAS, NVIS CANOPY WITH SUPERIOR LARGEST SURROUND VIEW INTERNAL FUEL TANK CAPACITY IN TRAINER CLASS ENDURANCE: >5.5 HOURS 15’’ CAMERA HATCH FOR MULTI ROLE OPERATION DOUBLE SLOTTED FLAPS FOR MAXIMUM LIFT LOW STALL SPEED SHORT LANDING DISTANCES LEADING EDGE DE - ICE SYSTEM FULL COMPOSITE AIRFRAME ALLOWS FOR SUPERB HARD POINTS AERODYNAMIC DESIGN ROBUST LANDING GEAR FOR UNPAVED SURFACE OPERATION TWO STATIONS PER WING SIDE COMPOSITE 5 BLADE PROPELLER PROVEN HIGH SPEED WING POWERED BY FUEL & COST EFFICIENT TURBINE (WIND TUNNEL TESTED UP TO M0.65) Page 5 DART VARIANTS DART-450 DART-550 Turboprop engine AI-450 CP (450 SHP) manufactured by Motor Turboprop aerobatic engine GE H75-A (550 SHP) manufactured by Sich. -
Version 1.4C
Nynja Build manual Version 1.4c 1 Nynja Build Manual 1.4b Figure 1 tube numbering scheme. 2 Nynja Build Manual 1.4b Figure 2 Basic frame (Skyranger). 3 Nynja Build Manual 1.4b Figure 3 uncovered Skyranger frame. 4 Nynja Build Manual 1.4b Figure 4 Uncovered Nynja frame Figure 5 Nynja fuselage with rear fairings removed 5 Nynja Build Manual 1.4b Figure 6 Nynja fuselage with rear fairings removed – rear view Figure 7 simply assemble thus! 6 Nynja Build Manual 1.4b Contents Introduction ............................................................................................................. 10 1.1 How to Build Your Aircraft .................................................................................................... 10 1.2 The BMAA Homebuilt Aircraft System ....................................................................................... 12 1.3 General Assembly Notes ........................................................................................................... 14 1.4 Finish .......................................................................................................................................... 18 1.5 Weight ........................................................................................................................................ 20 2. Forward Fuselage ............................................................................................ 21 2.1 Tube Numbering .................................................................................................................. 21