Radiolink At9s (Dsss&Fhss)
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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. -
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. -
Actuator Saturation Analysis of a Fly-By-Wire Control System for a Delta-Canard Aircraft
DEGREE PROJECT IN VEHICLE ENGINEERING, SECOND CYCLE, 30 CREDITS STOCKHOLM, SWEDEN 2020 Actuator Saturation Analysis of a Fly-By-Wire Control System for a Delta-Canard Aircraft ERIK LJUDÉN KTH ROYAL INSTITUTE OF TECHNOLOGY SCHOOL OF ENGINEERING SCIENCES Author Erik Ljudén <[email protected]> School of Engineering Sciences KTH Royal Institute of Technology Place Linköping, Sweden Saab Examiner Ulf Ringertz Stockholm KTH Royal Institute of Technology Supervisor Peter Jason Linköping Saab Abstract Actuator saturation is a well studied subject regarding control theory. However, little research exist regarding aircraft behavior during actuator saturation. This paper aims to identify flight mechanical parameters that can be useful when analyzing actuator saturation. The studied aircraft is an unstable delta-canard aircraft. By varying the aircraft’s center-of- gravity and applying a square wave input in pitch, saturated actuators have been found and investigated closer using moment coefficients as well as other flight mechanical parameters. The studied flight mechanical parameters has proven to be highly relevant when analyzing actuator saturation, and a simple connection between saturated actuators and moment coefficients has been found. One can for example look for sudden changes in the moment coefficients during saturated actuators in order to find potentially dangerous flight cases. In addition, the studied parameters can be used for robustness analysis, but needs to be further investigated. Lastly, the studied pitch square wave input shows no risk of aircraft departure with saturated elevons during flight, provided non-saturated canards, and that the free-stream velocity is high enough to be flyable. i Sammanfattning Styrdonsmättning är ett välstuderat ämne inom kontrollteorin. -
Stabilizer PLUS 7-Channel Receiver Essential Instructions
Lemon RX Stabilizer PLUS Receiver – Essential Instructions v1.1 Lemon RX Stabilizer PLUS 7-Channel Receiver Essential Instructions Contents Introducing the Lemon StabPLUS ............................................................................................................ 2 Functions ........................................................................................................................................................ 2 Transmitter Requirements .............................................................................................................................. 2 Servos and Power Sources .............................................................................................................................. 3 Setting up the StabPLUS ......................................................................................................................... 4 Installation ...................................................................................................................................................... 4 Binding ............................................................................................................................................................ 5 Setting Failsafe ................................................................................................................................................ 5 Test Flying .............................................................................................................................................. 6 Preparing -
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]. -
09 Stability and Control
Aircraft Design Lecture 9: Stability and Control G. Dimitriadis Introduction to Aircraft Design Stability and Control H Aircraft stability deals with the ability to keep an aircraft in the air in the chosen flight attitude. H Aircraft control deals with the ability to change the flight direction and attitude of an aircraft. H Both these issues must be investigated during the preliminary design process. Introduction to Aircraft Design Design criteria? H Stability and control are not design criteria H In other words, civil aircraft are not designed specifically for stability and control H They are designed for performance. H Once a preliminary design that meets the performance criteria is created, then its stability is assessed and its control is designed. Introduction to Aircraft Design Flight Mechanics H Stability and control are collectively referred to as flight mechanics H The study of the mechanics and dynamics of flight is the means by which : – We can design an airplane to accomplish efficiently a specific task – We can make the task of the pilot easier by ensuring good handling qualities – We can avoid unwanted or unexpected phenomena that can be encountered in flight Introduction to Aircraft Design Aircraft description Flight Control Pilot System Airplane Response Task The pilot has direct control only of the Flight Control System. However, he can tailor his inputs to the FCS by observing the airplane’s response while always keeping an eye on the task at hand. Introduction to Aircraft Design Control Surfaces H Aircraft control -
Recreational Flyer January - February 2010 Elevated: Angus Watt’S Ch-750
January - February 2010 Recreational Aircraft Association Canada www.raa.ca The Voice of Canadian Amateur Aircraft Builders $6.95 Elevated: Angus Watt's CH-750 Elevated: The original Zenith 701 was designed as an Angus Watt’s Ch-750 ultralight go-anywhere all metal bush plane that could be plans built by anyone with a 4 ft tabletop bending brake and a pair of snips. It was rarely described as a thing of beauty but so well does it fulfill its mission that these planes are found all over the world. They are inexpensive to construct, and because of their leading edge slats they can get in and out of extremely short patches of clear ground. 22 Recreational Flyer January - February 2010 Elevated: Angus Watt’s Ch-750 WITH THE ADVENT of the Light Sport category in and the only part interchangeable with the 701 is the US, Chris Heintz saw the need for an updated the signature Zenith all-flying rudder. Formerly the version, something with a larger cabin, greater skins were all .016” and they are now .020 to handle payload, and the ability to use an array of four the greater mass of the range of possible four stroke stroke engines. The CH 750 was the result and its engines and the 1320 pound gross weight on wheels, lineage is visually apparent but while the new plane 1430 on floats. resembles the 701 it is almost completely different in Chris Heintz correctly surmised that the US construction. CNC fabrication methods have made Light Sport category would be attractive to aging it possible to simplify the design, speed up the con- American pilots who wanted to bargain down to struction, and end up with a larger and faster plane their Sport Pilot category that allows a valid driver’s at only a slight weight penalty. -
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. -
Section 1 Introduction
INSTRUCTION MANUAL FOR AIRPLANE AND HELICOPTER XP6102 6-CHANNEL COMPUTER RADIO SYSTEM TABLE OF CONTENTS TABLE OF CONTENTS TABLE OF CONTENTS ......................2 CHAPTER 1: SOFTWARE FUNCTIONS – AIRPLANE ................11 Transmitter Callouts ..................12 CHAPTER 1: USING THIS MANUAL • INTRODUCTION ..............6 Transmitter Rear ......................13 Using this Manual ....................6 Direct Servo Control (DSC) ........14 R770 Receiver ..........................6 Control Stick Tension Adjustment ..14 Control Stick Length Adjustment ..14 Frequency Notes/ CHAPTER 2: FEATURES ....................6 Aircraft Only Frequencies ..........15 X-6102 Transmitter ....................6 Base Loaded Antenna ..............15 Transmitter Specifications ..........7 Neck Strap Attachment ..............15 System Specifications ................7 CHAPTER 2: CONNECTIONS • CHAPTER 3: COMPONENT AIRPLANE ..................16 SPECIFICATIONS ............7 Installation Requirements ..........16 S537 Ball Bearing Servo ..............7 Connections ..........................17 Airborne Battery Pack ................8 Backup Error Display ................18 Charger Specifications ................8 Receiver Specifications ..............8 CHAPTER 3: INPUT MODE AND Servo Specifications ..................8 FUNCTION • AIRPLANE ....18 Charger ..................................9 Key Input and Display ..............18 Transmitter/Receiver ..................9 System Mode ..........................19 Normal Mode ..........................19 CHAPTER 4: BATTERY