ACTIVE STICK & THROTTLE FOR F-35. Joseph Krumenacker NAVAIR Flight Controls / JSF Vehicle Systems 16 October 2008
|
|
- Madeline Nelson
- 1 years ago
- Views:
Transcription
1 ACTIVE STICK & THROTTLE FOR F-35 Joseph Krumenacker NAVAIR Flight Controls / JSF Vehicle Systems 16 October 2008
2 Intro Joe Krumenacker holds a BS in Aerospace & Mechanical Engineering from the University of Notre Dame, and previously worked for Grumman in aerodynamics, flight controls and flight test on the X-29 and F-14 programs. He joined the NAVAIR Flight Controls Branch in 1996 and has worked on the Joint Strike Fighter since He currently leads the JSF Program Office s Vehicle Control Integration team.
3 ACTIVE STICK & THROTTLE FOR F-35 Joseph Krumenacker NAVAIR Flight Controls / JSF Vehicle Systems 16 October 2008
4 JSF Active Inceptor System (AIS) Presentation Overview A. Why & What of Active Inceptors: JSF Inceptor Overview & Architecture Reconfiguration for AIS Degraded Modes AIS Specification Issues B. How have Active Inceptors been put to use: Current Uses of Active Capability Jetborne Advanced Modes Using Active Capability Lessons Learned C. Conclusions
5 Active Inceptor Overview As a system the AIS is partitioned into the following major elements Electronics Processor modules, motor drives, interfaces to FCC / grips Mechanics Gimbal assemblies, bearings, housings, seals & mountings Electromechanical Servo Actuator Units (SAUs), sensors Electronics Mechanics Electromechanical
6 Why Were Active Inceptors Chosen? Design Flexibility for STOVL Advanced Control Law JSF specification prohibits the use of a third inceptor and requires a pilot interface that minimizes both pilot workload and cognitive error potential. Throttle Back-drive Capability PA Approach Power Compensation (Auto-Throttle) UA Speed Hold Modes STOVL Performance Protection & Auto-Deceleration Modes Commonality Between CTOL, STOVL and CV Variants Active Stick & Throttle Had Already Been Proven on X-35 Demonstrator X-35 active throttle had a separate nozzle control lever
7 AIS Installation Overview SideStick (ASSCA) FWD Inceptor Control Unit (ICU) All JSF variants (CTOL, STOVL & CV) use identical AIS hardware & software. AIS is provided as a complete system by BAE, Rochester UK Stick & Throttle grips not procured as part of AIS. Throttle (ATQA)
8 Active Throttle (9-inch linear deflection) F-35 AA-1 Cockpit Active Side-Stick (approx. ±6 deg deflection)
9 Inceptor Characteristics Three Axes of Control: Stick Pitch, Stick Roll, Throttle Each Axis contains duplex 28V electric motor drives connected to grip interface by mechanical linkages Each Axis contains triplex force and position sensors Stick Axes contain mechanical springs for backup mode Grips (and various HOTAS switches) are supplied by separate vendor, but are qualified for flight together with the stick & throttle.
10 VMC & Inceptor Architecture ICU AIS SideStick VMC A (IEEE1394 network) Chan A (duplex motor interface) Pitch Axis VMC B Chan B Roll Axis VMC C Chan C Throttle Fore/Aft Each Vehicle Management Computer (VMC) Contains: CLAW Application which determines inceptor force gradients and other features FCRM Application to manage ICU health & failure reports and to select triplex inceptor position & forces for CLAW input Inceptor Control Unit (ICU) performs: Motor Drive Loop Closure & Control Failure Management Mode Control Initiated Built-In Test (triplex grip force & position feedbacks)
11 AIS Modes & Fault Accommodation Each Inceptor has three primary control modes: Active: sensed grip force is used to actively position the inceptor according to the programmed force vs. position characteristics Flight Control Laws use inceptor position as pilot command Passive: motor drives disengaged, stick springs provide fixed linear force gradient, throttle has fixed friction & no detents Used upon unrecoverable error with motor drives Flight Control Laws use stick forces and throttle position as pilot command Both stick axes will maintain like mode (if one axis downgrades passive mode, other axis will be place passive mode) Jammed: inceptor position is fixed automatically detected by software Flight Control Laws use inceptor force as pilot command jammed throttle requires some Control Law reconfiguration
12 Active Inceptor Requirements & Specification Issues Programmable Inceptor Active Mode Characteristics: force gradients/ramps forward & aft end stops variable damping force gates & soft-stops (e.g AB) pilot-adjustable friction force (throttle) force detents (STOVL) position back-drive (autothrottle modes) Inceptor Specification Issues: force capability (static and dynamic) force accuracy/variability velocity capability motor drive redundancy electronics redundancy force sensor null drift & sensor noise characteristics passive mode centering (stick) passive mode breakout and force gradients (stick) Blue shaded items are less configuration-dependent than others and could benefit from industry-wide specifications or guidance.
13 How Is Active Capability Currently Used? Throttle: Variable aft & forward end-stops (e.g. STOVL mode is different from CTOL mode) AB gate (when STOVL system is not deployed) Launch gate (CV only) STOVL center detent (zero commanded acceleration) STOVL on-ground power braking force gradient Back-drive Auto-Throttle Approach (all variants) STOVL Decel-to-Hover
14 How Is Active Capability Currently Used? Stick: Tailored STOVL pitch force characteristics wingborne vs. jetborne variations forward soft-stop(s) for vertical landing sink speed Pitch force feedback at higher AOA Roll force tailoring: left vs. right Roll force tailoring: CTOL vs. STOVL Increased force breakout for CV launch (pitch & roll) Pitch Stick Force Fwd CTOL STOVL - Wingborne STOVL - Jetborne Pitch Stick Deflection Aft
15 Background: F-35B Jetborne Control Strategy Left-Hand Inceptor (LHI) provides fore/aft acceleration control (with speed hold function on center detent) Lateral Right-Hand Inceptor (RHI) provides bank angle control to give lateral acceleration Longitudinal Right-Hand Inceptor (RHI) provides height rate control (zero force commands altitude hold) Full matrix of STOVL tasks can be flown by using only the two primary inceptors in a consistent manner throughout the flight envelope. Nozzle / thrust vector control not required in flight Cognitive error potential minimized by consistent inceptor functionality HOTAS functions can be added to provide additional hover control options
16 Further Advancements Using Active Inceptors: TRC Mode TRC = Translational Rate Command LHI (Throttle) Characteristics LHI Force (lbs) Lateral RHI (Stick) Characteristics RHI Force (lbs) Disengage Stop 20 Disengage Stop Disengage Stop 20 Disengage Stop Decel Cmd 10 Accel Cmd Bank Cmd 10 Bank Cmd AFT 1 LHI Displacement 1 FWD (inches) LEFT 5 4 RHI Displacement 4 5 (deg) RIGHT Velocity Command (kts) 10 Velocity 10 Command (kts) Engage / Disengage via HOTAS Switch Velocity Trim via Speedbrake switch Disengage via Force Breakout Disengage via Paddle Switch
17 Potential Option for Longitudinal Stick: Height Gripper Proposed Change to Jetborne Height Axis: Pitch Stick would command altitude acceleration instead of the baseline altitude rate. releasing the stick would no longer command zero sink rate (altitude-hold), so some other means of low-workload height hold was required solution was a pilot-engageable gripper mode, in which an altitude-hold augmentation could be quickly engaged and disengaged with gripper engaged, longitudinal stick breakout force is significantly increased to prevent inadvertent disengagement Altitude Rosette is Boxed on Engagement Manual Disengage to start descent rate Pros Hover stick force is significantly higher and provides pilot direct tactile feedback and confirmation that the flight control system is in control of height axes Push through or paddle off to begin vertical landing Cons Remembering to select height hold More buttons required Boxed Altitude Engaged with S-5 switch Altitude Gripper Breakout: +/- 20 lbs -or - NWS Button
18 AIS Lessons Learned Level 1 flying qualities for precise STOVL tasks are possible using a small, limited-displacement stick, due to the ability to set jetborne-specific stick characteristics without compromising wingborne flying qualities. Passive and jammed modes can be accommodated with only minor flying qualities degradations throttle control in jammed mode perhaps the greatest challenge Inceptor back-drive capability can be used to provide critical insight and training to the pilot in a very intuitive manner power approach auto-throttle as a training aid STOVL auto-decel and performance deficit protection (potential) high AOA cueing
19 Conclusions JSF is committed to use of active inceptor system (AIS) for all three aircraft variants production-representative AIS has been flying on AA-1 aircraft since December AIS has provided a valuable level of design flexibility both for the existing vehicle control laws and for the resolution of any yet unknown flying qualities shortcomings. AIS team has been challenged by environmental requirements for force sensors, and has worked hard to ensure force feel characteristics and redundancy management meet vehicle needs.
20 Questions?
The most important thing we build is trust. HeliSAS Technical Overview
The most important thing we build is trust HeliSAS Technical Overview HeliSAS Technical Overview The Genesys HeliSAS is a stability augmentation system (SAS) and two-axis autopilot that provides attitude
FLIGHT CONTROLS SYSTEM
FLIGHT CONTROLS SYSTEM DESCRIPTION Primary flight control of the aircraft is provided by aileron, elevator and rudder control surfaces. The elevator and rudder control surfaces are mechanically operated.
Analysis of JSF Prototypes
Analysis of JSF Prototypes By: Timothy D. Collins Photo from: http://www.popsci.com/scitech/features/xplane/index.html Boeing X-32 on Left, and Lockheed-Martin X-35 on Right. These two aircraft are designed
F135 Propulsion Integration Topics for Symposium on Jet Engines Haifa, Israel
F135 Propulsion Integration Topics for Symposium on Jet Engines Haifa, Israel Tom Johnson Program Chief Engineer Operational Military Engines 25 October 2012 J6924_F135_Propulsion_2012-1 Agenda F135 Development
MULTIBODY ANALYSIS OF THE M-346 PILOTS INCEPTORS MECHANICAL CIRCUITS INTRODUCTION
MULTIBODY ANALYSIS OF THE M-346 PILOTS INCEPTORS MECHANICAL CIRCUITS Emanuele LEONI AERMACCHI Italy SAMCEF environment has been used to model and analyse the Pilots Inceptors (Stick/Pedals) mechanical
NASA Offices and Research GegteFs.
INITIAL RESULTS OF STUDIES OF HANDLING QUALITIES OF A SIMULATED LUNAR LANDING VEHICLE By Thomas C. O'Bryan NASA Langley Research Center Langley Station, Hampton, Va. Presented at the SAE Committee A-18
General. Lateral Control System. Longitudinal Control System
Flt.0 Flight Controls-Description and Operation General All primary and secondary flight controls are hydraulically powered, each by at least two, and in some cases, by all three airplane hydraulic systems.
F/A-18A/B/C/D Flight Control Computer Software Upgrade
F/A-18A/B/C/D Flight Control Computer Software Upgrade V10.7 Military Aircraft System Verification and Validation MIT 16.885J/ESD.35J Fall 2004 CDR Paul Sohl Commanding Officer United States Naval Test
Flight Test Evaluation of C-130H Aircraft Performance with NP2000 Propellers
Flight Test Evaluation of C-130H Aircraft Performance with NP2000 Propellers Lance Bays Lockheed Martin - C-130 Flight Sciences Telephone: (770) 494-8341 E-Mail: lance.bays@lmco.com Introduction Flight
System Normal Secondary Direct. All 3 PFC work in parallel. available. Pitch Normal Secondary Direct. Pitch maneuver command.
Flight s System Normal Secondary Direct Primary Flight Computers (PFC) Three Primary Flight Computers use control wheel and pedal inputs from the pilot to electronically the primary flight control surfaces
XIV.C. Flight Principles Engine Inoperative
XIV.C. Flight Principles Engine Inoperative References: FAA-H-8083-3; POH/AFM Objectives The student should develop knowledge of the elements related to single engine operation. Key Elements Elements Schedule
Operational Liaison Meeting FBW aircraft. Avoiding Tail Strike
Operational Liaison Meeting FBW aircraft Avoiding Tail Strike Content Statistics Most common causes Factors affecting the margins Aircraft design features Operational recommendations Conclusions Statistics
A brief History of Unmanned Aircraft
A brief History of Unmanned Aircraft Technological Background Dr. Bérénice Mettler University of Minnesota Jan. 22-24, 2012 (v. 1/15/13) Dr. Bérénice Mettler (University of Minnesota) A brief History of
Severe Service Hydraulic Actuators for the Nuclear Power Industry. Enertech Nuclear Qualified Electro-Hydraulic Actuators
Severe Service Hydraulic Actuators for the Nuclear Power Industry Enertech Nuclear Qualified Electro-Hydraulic Actuators Engineered Solutions for the Nuclear Power Industry Enertech, formerly Paul Munroe
Effect of ZFW / ZFWCG on Aircraft Operations
Operational Liaison Meeting Fly-By-Wire Aircraft 2004 Effect of / on Aircraft Operations Customer Services Contents Single-Aisle (SA) FM Architecture FAC Computation If Incorrect entered on the If Incorrect
AT-10 Electric/HF Hybrid VTOL UAS
AT-10 Electric/HF Hybrid VTOL UAS Acuity Technologies Robert Clark bob@acuitytx.com Summary The AT-10 is a tactical size hybrid propulsion VTOL UAS with a nose camera mount and a large payload bay. Propulsion
Section 1 Systems Descriptions
1 Section 1 Systems Descriptions The Pro Flight Trainer PUMA is a single pilot, modifiable to dual Pilot, 8 axes HID USB Helicopter Control Device that provide advanced immersion in a realistic helicopter
UH-60M Upgrade Fly-By-Wire Flight Control Risk Reduction Using the RASCAL JUH-60A In-Flight Simulator
UH-6M Upgrade Fly-By-Wire Flight Control Risk Reduction Using the RASCAL JUH-6A In-Flight Simulator Dave Arterburn U.S. Army Utility Helicopters Program Office Redstone Arsenal, AL Chan Morse Morse Flight
QuickStick Repeatability Analysis
QuickStick Repeatability Analysis Purpose This application note presents the variables that can affect the repeatability of positioning using a QuickStick system. Introduction Repeatability and accuracy
Hydraulic Proportional and Closed Loop System Design
Hydraulic Proportional and Closed Loop System Design Neal Hanson Product Manager Industrial Valves and Electrohydraulics 1 Electrohydraulics Contents 1. Electrohydraulic Principles 2. Proportional Valve
International Journal of Scientific & Engineering Research, Volume 4, Issue 7, July ISSN BY B.MADHAN KUMAR
International Journal of Scientific & Engineering Research, Volume 4, Issue 7, July-2013 485 FLYING HOVER BIKE, A SMALL AERIAL VEHICLE FOR COMMERCIAL OR. SURVEYING PURPOSES BY B.MADHAN KUMAR Department
Presse-Information. The mycopter project points the way towards Personal Aerial Vehicles
The mycopter project points the way towards Personal Aerial Vehicles Road congestion is a fact of everyday life for many people. A possible solution for the future is expanding personal transport to include
THE FALCON I LAUNCH VEHICLE Making Access to Space More Affordable, Reliable and Pleasant
18 th Annual AIAA/USU Conference on Small Satellites SSC04-X-7 THE FALCON I LAUNCH VEHICLE Making Access to Space More Affordable, Reliable and Pleasant Hans Koenigsmann, Elon Musk, Gwynne Shotwell, Anne
SECTION 2-13 FLIGHT CONTROLS
SECTION 2-13 TABLE OF CONTENTS Block General... 2-13-05..01 Pitch Control... 2-13-10..01 General... 2-13-10..01 Elevator... 2-13-10..02 General... 2-13-10..02 Jammed Elevator... 2-13-10..02 Jammed Elevator
Throttle Quadrant Operating Manual English Version
Throttle Quadrant Operating Manual English Version Cockpitsonicversion1 Page1 Contents 1. Introduction... 3 2. Installation... 3 3. Calibration... 5 4. Using Your Throttle Quadrant... 9 5. Contact Details...
B737 Performance. Takeoff & Landing. Last Rev: 02/06/2004
B737 Performance Takeoff & Landing Last Rev: 02/06/2004 Takeoff Performance Takeoff Performance Basics Definitions: Runway Takeoff Distances Definitions: Takeoff Speeds JAR 25 Requirements Engine failure
At all times use approved company publications and aircraft manufacturer manuals as sole reference for procedures and data!
Disclaimer These notes have not been approved by any aviation administration, by any airline nor by the aircraft manufacturer to whom it refers. At all times use approved company publications and aircraft
AERONAUTICAL DESIGN STANDARD PERFORMANCE SPECIFICATION HANDLING QUALITIES REQUIREMENTS FOR MILITARY ROTORCRAFT
INCH-POUND ADS-33E-PRF 21 March 2000 CAGE Code 18876 SUPERSEDING ADS-33D-PRF 10 May 1996 AERONAUTICAL DESIGN STANDARD PERFORMANCE SPECIFICATION HANDLING QUALITIES REQUIREMENTS FOR MILITARY ROTORCRAFT AMSC
Full-Scale 1903 Wright Flyer Wind Tunnel Test Results From the NASA Ames Research Center
Full-Scale 1903 Wright Flyer Wind Tunnel Test Results From the NASA Ames Research Center Henry R. Jex, Jex Enterprises, Santa Monica, CA Richard Grimm, Northridge, CA John Latz, Lockheed Martin Skunk Works,
NORWAY Industrial Participation. 25 January 2007
NORWAY Industrial Participation 25 January 2007 1 Agenda Topics Overview Basis of Estimates LM Aero & JSF Team Projects! Current Contracted & Committed! Additional Production Related! Global Sustainment
Appenidix E: Freewing MAE UAV analysis
Appenidix E: Freewing MAE UAV analysis The vehicle summary is presented in the form of plots and descriptive text. Two alternative mission altitudes were analyzed and both meet the desired mission duration.
Climber is 776B101101
is Climber 776B101101 Introduction Product Introduction NE R/C 776B is a good-sized glider designed by Nine Eagles Company latest, whose wing span is up to 2008mm. You only need to assemble the aerofoil
Bild : Bernhard Mühr German Aerospace Center Flight Operations
German Aerospace Center Flight Operations Bild : Bernhard Mühr www.wolkenatlas.de Introduction DLR is Germany s aerospace research center and space agency with about 4700 employees in 31 research institutes
Compatibility of STPA with GM System Safety Engineering Process. Padma Sundaram Dave Hartfelder
Compatibility of STPA with GM System Safety Engineering Process Padma Sundaram Dave Hartfelder Table of Contents Introduction GM System Safety Engineering Process Overview Experience with STPA Evaluation
How to use the Multirotor Motor Performance Data Charts
How to use the Multirotor Motor Performance Data Charts Here at Innov8tive Designs, we spend a lot of time testing all of the motors that we sell, and collect a large amount of data with a variety of propellers.
9303 PROGRAM MIX EXAMPLES
9303 PROGRAM MIX EXAMPLES Here are a few examples of some common program mixes. They are intended as a quick reference guide and may require modification to suit a particular installation. SMOKE SYSTEM
EMERGENCY PROCEDURES SECTION I. HELICOPTER SYSTEMS
9-1. HELICOPTER SYSTEMS. EMERGENCY PROCEDURES SECTION I. HELICOPTER SYSTEMS This section describes the helicopter systems emergencies that may reasonably be expected to occur and presents the procedures
SKY RAIDER INSTRUCTION BOOKLET. 2.4Ghz Indoor / Outdoor Battling Quadrocopter
FCC Part 15 C Notice CAUTION: Changes or modifications not expressly approved by the party responsible for compliance could void the user s authority to operate the equipment. NOTE: This equipment has
Lunette: A Global Network of Small Lunar Landers
Lunette: A Global Network of Small Lunar Landers Leon Alkalai and John O. Elliott Jet Propulsion Laboratory California Institute of Technology LEAG/ILEWG 2008 October 30, 2008 Baseline Mission Initial
Facts, Fun and Fallacies about Fin-less Model Rocket Design
Facts, Fun and Fallacies about Fin-less Model Rocket Design Introduction Fin-less model rocket design has long been a subject of debate among rocketeers wishing to build and fly true scale models of space
Multi-ECU HiL-Systems for Virtual Characteristic Rating of Vehicle Dynamics Control Systems
Multi-ECU HiL-Systems for Virtual Characteristic Rating of Vehicle Dynamics Control Systems Dipl.-Ing. Ronnie Dessort, M.Sc. Philipp Simon - TESIS DYNAware GmbH Dipl.-Ing. Jörg Pfau - Audi AG VDI-Conference
A LIGHTWEIGHT, LOW LEAKAGE PIEZOELECTRIC SERVOVALVE
A LIGHTWEIGHT, LOW LEAKAGE PIEZOELECTRIC SERVOVALVE PERSSON L. Johan PLUMMER Andrew BOWEN Chris Centre for Power Transmission and Motion Control, Department of Mechanical Engineering, University of Bath,
Dealing with customer concerns related to electronic throttle bodies By: Bernie Thompson
Dealing with customer concerns related to electronic throttle bodies By: Bernie Thompson In order to regulate the power produced from the gasoline internal combustion engine (ICE), a restriction is used
Resilient-EGI Prototype Pilot: Common Application Space Prototype Pilot
Resilient-EGI Prototype Pilot: Common Application Space Prototype Pilot Robert P. decourcy Jeffrey Wallace 1, Sara J. Kambouris 1, Jacob Campbell 2, Christopher Garrett 3, M. Dean Garvey 1 1-Infinite Dimensions
Mig-29A FulcrumA & Mig-29S FulcrumC Short range air to air fighter with limited air to ground capability.
Lock-On Modern Air Combat Check-lists Mig-29A FulcrumA & Mig-29S FulcrumC Short range air to air fighter with limited air to ground capability. Not suited for Real Operations For Lomac use only. Each lomac
CIVIL AVIATION AUTHORITY SAFETY REGULATION GROUP MICROLIGHT TYPE APPROVAL DATA SHEET (TADS) NO: BM 41 ISSUE: 7
TYPE: Shadow Series CD (1) MANUFACTURER CFM Aircraft Ltd (ceased trading) BMAA is responsible for continued airworthiness (2) UK IMPORTER None (3) CERTIFICATION BCAR Section S (First example Advanced Issue
CIVIL AVIATION AUTHORITY SAFETY REGULATION GROUP MICROLIGHT TYPE APPROVAL DATA SHEET (TADS) NO: BM 41 ISSUE: 7. Shadow Series CD
Shadow Series CD 1 MANUFACTURER CFM Aircraft Ltd (ceased trading) BMAA is responsible for continued airworthiness 2 UK IMPORTER None 3 CERTIFICATION BCAR Section S (First example Advanced Issue dated March
Cam Motion Case Studies #1 and # 2
Cam Motion Case Studies #1 and # 2 Problem/Opprtunity: At an operating speed of 150 to 160 rpm, Cam Motion #1 causes the cam follower to leave the cam surface unless excessive air pressure is applied to
A practical investigation of the factors affecting lift produced by multi-rotor aircraft. Aaron Bonnell-Kangas
A practical investigation of the factors affecting lift produced by multi-rotor aircraft Aaron Bonnell-Kangas Bonnell-Kangas i Table of Contents Introduction! 1 Research question! 1 Background! 1 Definitions!
Clean Sky 2. LifeCraft Demonstrationt (IADP RC 2 & ITDs) Consultation meetings Brussels th December 2012 OUTLINE
Clean Sky 2 LifeCraft Demonstrationt (IADP RC 2 & ITDs) Consultation meetings Brussels 10-14 th December 2012 1 1 LifeCraft - The Compound Demo OUTLINE Presentation of the Compound R/C Concept Impact &
CHAPTER 29 HYDRAULICS Description Hydraulic Pump Hydraulic Reservoir Hydraulic Servos
Section Title CHAPTER 29 HYDRAULICS 29-00 Description............................................... 29.1 29-10 Hydraulic Pump............................................ 29.1 29-20 Hydraulic Reservoir.........................................
Mathew S. Antony. Submitted in partial fulfillment of the. requirements for Departmental Honors in. the Department of Science and Engineering
TACTILE LIMIT CUEING SYSTEMS FOR ROTORCRAFT FLIGHT CONTROL by Mathew S. Antony Submitted in partial fulfillment of the requirements for Departmental Honors in the Department of Science and Engineering
Application Note CTAN #234
Application Note CTAN #234 The Application Note is pertinent to the Unidrive SP Family A Guide to Tuning the Unidrive SP Introduction: The Unidrive SP provides a number of features that greatly assist
Electric Drive - Magnetic Suspension Rotorcraft Technologies
Electric Drive - Suspension Rotorcraft Technologies William Nunnally Chief Scientist SunLase, Inc. Sapulpa, OK 74066-6032 wcn.sunlase@gmail.com ABSTRACT The recent advances in electromagnetic technologies
Electromechanical Tilting Systems for Passenger Trains
for Passenger Trains Stabilization Systems Leading the world market Tomorrow s Technology Today Who we are... ESW holds the leading position in the world market for electro mechanical tilting technology
Document No. ST-931-RFM-0001
275 Palos Verdes Dr. North Document No. ST-931-RFM-1 FAA APPROVED Rotorcraft Flight Manual Supplement to the Robinson R44 Pilot s Operating Handbook and FAA Approved Rotorcraft Flight Manual HeliSAS Aircraft
FLASHCARDS AIRCRAFT. Courtesy of the Air Safety Institute, a Division of the AOPA Foundation, and made possible by AOPA Services Corporation.
AIRCRAFT FLASHCARDS Courtesy of the Air Safety Institute, a Division of the AOPA Foundation, and made possible by AOPA Services Corporation. Knowing your aircraft well is essential to safe flying. These
Welcome to the Airbus A380 Basic Manual for Virtual Air Cadet Airlines.
Welcome to the Airbus A380 Basic Manual for Virtual Air Cadet Airlines. Performance figures: Max operating speed: 340kts / M0.89 Max gear speed: 250kts / M0.55 Max flap speeds: Code: Select all Flaps Speed
This manual is for all versions of the F9F Panther This Manual uses one color scheme as an example
This manual is for all versions of the This Manual uses one color scheme as an example Thank you for purchasing the. This model is designed for the intermediate to advanced flyer. The model is receiver-ready
(Original signatures are on file with official student records.)
To the Graduate Council: I am submitting herewith a thesis written by Matthew E. Doyle entitled Retrofit Reconfigurable Flight Control System and the F/A-18C. I have examined the final electronic copy
Transition to Unleaded Fuels for General Aviation
Transition to Unleaded Fuels for General Aviation Pervez Canteenwalla, Malcolm Imray, Peter Earle, and Wajid Chishty NRC Aerospace UTIAS National Colloquium on Sustainable Aviation June 21-23, 2017 Current
FLIGHT TEST PROGRAM YOUR AIRPLANE HERE FLIGHT TEST PROGRAM YOUR AIRPLANE HERE
Flight #: 1 FIRST TEST FLIGHT Validate Engine Reliability Explore Flight Control Characteristics Do not use flaps Do not change throttle settings, mixture, or fuel tanks Remain above the airport Climb
FUEL CONSERVATION. WG4 Workshop Aviation Operational Measures for Fuel & Emissions Reductions. Philippe Fonta AIRBUS
WG4 Workshop Aviation Operational Measures for Fuel & Emissions Reductions Philippe Fonta AIRBUS Ottawa, 5-6 November 2002 1 28 October 1972: Maiden flight of the A300 1973: First energy crisis Airbus
SECTION II AIRPLANE AND SYSTEMS MODEL 750 HYDRAULIC
HYDRAULIC The main hydraulic system is comprised of two independent systems; system A and system B. Hydraulic power is used to power the primary flight controls (rudder, elevators, ailerons, and roll spoilers),
New Design Concept of Compound Helicopter
New Design Concept of Compound Helicopter PRASETYO EDI, NUKMAN YUSOFF and AZNIJAR AHMAD YAZID Department of Engineering Design & Manufacture, Faculty of Engineering, University of Malaya, 50603 Kuala Lumpur,
Flap Positioning Systems available with or without Automatic Elevator Trim
Flap Positioning Systems available with or without Automatic Elevator Trim without Auto Elevator Trim with Automatic Elevator Trim Designed for RV-10 s (eliminates stick back pressure) and Flap Systems
Basic hypothesis. Subjective position may give less Drag at high Mach number to the Typhoon and better Lift at high AoA (>20) for the Rafale.
vs Rafale Basic hypothesis Rafale C and share the same aerodynamic configuration, means same CL (lift) and CD (drag) coefficients law [Cx(Mach, AoA)]. This is known as not realistic, but I do not have
PA34-220T Piper Seneca III
PREFLIGHT PA34-220T Piper Seneca III Weight and Balance Documents -Airworthiness Certificate -Registration -Airplane Flight Manual -Weight & Balance Hobbs/Time Landing Gear Avionics and Fan(s) Cowl Fuel
Controls DEA 3250/6510. Controls are a frequent source of system error and failure.
Controls Controls DEA 3250/6510 Controls are a frequent source of system error and failure. Controls - Simplicity in Design Complex controls invariably can be simplified by ergonomic analysis. Controls
COMPATIBLE MOTOR ASSEMBLY TYPES
4908 McKenna Ct., Columbus, Ohio, 43221 USA (614) 876-6345 www.aircraftextras.com sales@aircraftextras.com INSTALLATION MANUAL THANK YOU!... for purchasing the FPS-Plus system from Aircraft Extras, Inc.
NASA s Choice to Resupply the Space Station
RELIABILITY SpaceX is based on the philosophy that through simplicity, reliability and low-cost can go hand-in-hand. By eliminating the traditional layers of management internally, and sub-contractors
LESSON 2 BASIC CONSTRUCTION AND OPERATION OF HYDRAULIC ACTUATING DEVICES, FLOW CONTROL, AND DIRECTIONAL DEVICES. STP Tasks:
LESSON 2 BASIC CONSTRUCTION AND OPERATION OF HYDRAULIC ACTUATING DEVICES, FLOW CONTROL, AND DIRECTIONAL DEVICES STP Tasks: 552-758-1003 552-758-1071 OVERVIEW LESSON DESCRIPTION: In this lesson you will
Redbird Insight User Guide
Redbird Insight User Guide 1 Copyright 2012 Redbird Flight Simulations Contents Welcome... 3 System Requirements... 4 QUICK START GUIDE...5 Video Display... 6 Support Ethernet Port... 7 Insight DVR Application
Sheffield Hallam University Engineering Masterclass Programme 2015
Sheffield Hallam University For more information please contact Helen King Special Projects Officer Engineering and Tel: 0114 225 6459 Email: h.king@shu.ac.uk An overview We are excited to launch Sheffield
Modification of IPG Driver for Road Robustness Applications
Modification of IPG Driver for Road Robustness Applications Alexander Shawyer (BEng, MSc) Alex Bean (BEng, CEng. IMechE) SCS Analysis & Virtual Tools, Braking Development Jaguar Land Rover Introduction
PROJECT HAVE DOUGHNUT -
Foreign Technology Division PROJECT HAVE DOUGHNUT - EXPLOITATION OF THE MIG-21 Rob Young Historian National Air and Space Intelligence Center This Briefing is Classified: UNCLASSIFIED//APPROVED FOR PUBLIC
The Synaptic Damping Control System:
The Synaptic Damping Control System: increasing the drivers feeling and perception by means of controlled dampers Giordano Greco Magneti Marelli SDC Vehicle control strategies From passive to controlled
SK-GPS Instruction Manual. Rev August 1, 2014
SK-GPS Instruction Manual Rev. 1.10 August 1, 2014 Table of Contents Safety...1 Box Contents...2 Getting Started...3 SK-GPS Internal Blue LED States...3 Swash Bump at Init...3 Mounting the SK-GPS...4 Connecting
New Technologies for Green Rotorcraft GRDC Symposium 2011 Seoul, 15 th November 2011
New Technologies for Green Rotorcraft GRDC Symposium 2011 Seoul, 15 th November 2011 K. PAHLKE Head DLR Rotorcraft Programme Slide 1 Outlook Overview on DLR Rotorcraft Research Programme in Cooperation
The electro-mechanical power steering with dual pinion
Service Training Self-study programme 317 The electro-mechanical power steering with dual pinion Design and function The electro-mechanical power steering has many advantages over the hydraulic steering
FTE automotive Innovation drives. Transmission actuation. hydraulic and electromechanical components for automatic transmissions
FTE automotive Innovation drives Transmission actuation hydraulic and electromechanical components for automatic transmissions 1 Innovative elements for the current development trend Transmission actuators
Micro Craft Ducted Air Vehicle. Larry Lipera istar Program Manager Micro Craft Inc., San Diego, CA
Micro Craft Ducted Air Vehicle Larry Lipera istar Program Manager (llipera@microcraft.com) Micro Craft Inc., San Diego, CA Abstract Recent military and commercial interest in Unmanned Air Vehicles has
ROBINSON MODEL R-44 HELICOPTER TRACK AND BALANCE
Application Note AN-MV2-R44 Rev 02-10 May 2012 MicroVib II Aircraft Analyzer Helicopter Track and Balance ROBINSON MODEL R-44 HELICOPTER TRACK AND BALANCE Dynamic Solutions Systems, Inc. (760) 598-4000
PRECISION BELLOWS COUPLINGS
PRECISION BELLOWS COUPLINGS Bellows couplings are used where precise rotation, high speeds, and dynamic motion must be transmitted. They exhibit zero backlash and a high level of torsional stiffness, offering
CIVIL AVIATION AUTHORITY SAFETY REGULATION GROUP MICROLIGHT TYPE APPROVAL DATA SHEET (TADS) NO: BM 19 ISSUE: 6. Shadow Series BD
Shadow Series BD 1 MANUFACTURER CFM Aircraft Ltd (ceased trading) BMAA is responsible for continued airworthiness 2 UK IMPORTER None 3 CERTIFICATION BCAR Section S Advance Issue dated March 1983. List
Monitoring of Shoring Pile Movement using the ShapeAccel Array Field
2359 Royal Windsor Drive, Unit 25 Mississauga, Ontario L5J 4S9 t: 905-822-0090 f: 905-822-7911 monir.ca Monitoring of Shoring Pile Movement using the ShapeAccel Array Field Abstract: A ShapeAccel Array
AIRCRAFT BRAKE TESTING
AIRCRAFT BRAKE TESTING ALPA 52 nd Annual Air Safety Forum Captain John E. Cashman Director Flight Crew Operations The Boeing Company Agenda Terminology Certified vs. Advisory data Brake testing (Lab and
LAA TYPE ACCEPTANCE DATA SHEET TADS 193 RANS S4 AND RANS S5 (B WING AND C WING)
Issue 2 MOD/193/006 added, ref tail bracing wire tang cracking. dated 13.06.07 1. UK contact Skycraft Ltd., Kestrel, Broadgate, Weston Hills, Spalding. Lincs. PE12 6DP. United Kingdom Telephone: 01406
University of Colorado Model Positioning - DynAmic/Static - System. Preliminary Design Review 13 October 2015
University of Colorado Model Positioning - DynAmic/Static - System Preliminary Design Review 13 October 2015 Nicholas Gilland, Brandon Harris, Kristian Kates, Ryan Matheson, Amanda Olguin, Kyle Skjerven,
Adrestia. A mission for humanity, designed in Delft. Challenge the future
Adrestia A mission for humanity, designed in Delft 1 Adrestia Vision Statement: To inspire humanity by taking the next step towards setting a footprint on Mars Mission Statement Our goal is to design an
Section 18: Fuses, Heaters, Parameters
Section 18: Fuses, Heaters, Parameters March 2003 Section 18: Fuses, Heaters, Parameters 639 640 Section 18: Fuses, Heaters, Parameters March 2003 March 2003 Section 18: Fuses, Heaters, Parameters 641
INSTALLATION MANUAL AND OPERATING INSTRUCTIONS XX and XX Series Electric Attitude Indicator
INSTALLATION MANUAL AND OPERATING INSTRUCTIONS 4300-3XX and 4300-5XX Series Electric Attitude Indicator MID-CONTINENT INST. CO., INC MANUAL NUMBER 9015692 Copyright 2003 Mid-Continent Instrument Co., Inc.
BFF Motorised Trim Wheel - Set-up
BFF Motorised Trim Wheel - Set-up Table of Contents Summary of Set-up Steps...1 BFF Motorised Trim Wheel - Setup Details...2 Final Set-Up For Direct Connection To FSUIPC/XPUIPC...5 Final Set-Up For Direct
Flight Control Systems
1 Flight Control Systems 1.1 Introduction Flight controls have advanced considerably throughout the years. In the earliest biplanes flown by the pioneers flight control was achieved by warping wings and
F-5E Tiger II USER MANUAL. Virtavia F-5E Tiger II DTG Steam Edition Manual Version 2.0
F-5E Tiger II USER MANUAL 0 Introduction The F-5E Tiger II is an improved version of the original F-5 Freedom Fighter that entered service with the US Military in the early 1960s. It is a lightweight,
Schilling Robotics CONAN 7P Manipulator
Schilling Robotics CONAN 7P Manipulator We put you first. And keep you ahead. The CONAN s combination of high strength and low cost make it the manipulator of choice for medium and heavy-work class ROVs.
w w w. o n e r a. f r
www. onera. fr Pioneering concepts for Personal Air Transport Systems PPlane Project AMPERE Project Hybrid electrical propulsion study PPlane : a pioneering concept for Personal Air Transport Systems The
Welcome to Vibrationdata
Welcome to Vibrationdata Acoustics Shock Vibration Signal Processing September 2010 Newsletter Cue the Sun Feature Articles This month s newsletter continues with the space exploration theme. The Orion
Hydraulic Drives: How to Combine Dynamics and Efficiency. Bert Brahmer,
Hydraulic Drives: How to Combine Dynamics and Efficiency Bert Brahmer, 2011-04-21 Contents 1. Introduction 2. Benefits of Hydraulics in Industrial Drives 3. Challenges for Hydraulics 4. HPPC: Highly Dynamic
3. What is the total fuel capacity with normal tanks? Usable? 4. What is the total fuel capacity with long range tanks? Usable?
Pilot Name: Last, first, mi. Date: (mo/dy/yr) Instructor: Pass/Fail: Instructors Initials: 1. What is the engine Manufacturer: Model: Type: 2. What is the horsepower rating? 3. What is the total fuel capacity