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  • Stability and Control » Aircraft Research Association
    Services Precision Model Manufacture Inspection Services Finite Element Analysis Strain Gauge Balance Design and Manufacture Mécanique des Fluides Numérique CFD Software Code Development CFD Software Code Application Applied Aerodynamics Integrated CFD Wind Tunnel Weapons and Weapon Bay Analysis Wing Design Process Aerodynamic Research Innovation et technologie Clean Sky Project Strain Gauge Balance Developments Pressure Sensitive Paint Model Deformation Measurement New Page fr Media Centre Image Library Video Gallery Document Downloads Newsletter Registration Careers Vacancies New Page fr New Page fr New Page fr New Page fr Benefits Apprentices Personal Experiences Graduates Industrial Placements Work Experience Contact Stability and Control Aircraft Research Association Services Aérodynamique Expérimentale Transonic Wind Tunnel Testing Civil Aircraft Stability and Control A typical civil aircraft is kept stable by a horizontal tail and a vertical fin The aircraft is controlled in roll by ailerons on the wings in pitch by an elevator on the horizontal tail plane and in yaw by a rudder on the vertical fin It is critical to the safety of the aircraft that the control surfaces perform their function throughout the operational envelope at all speeds and attitudes A Typical Test Wind tunnel tests enable aircraft designers to check how an aircraft model performs both within and beyond its operational envelope in a safe and controlled environment A typical test may involve the design and manufacture of control surfaces such as spoilers or ailerons larger items such as engine nacelles and pylons or the complete aircraft model followed by a wind tunnel test The aerodynamic loads on individual components can be measured by attaching each component to the parent aircraft with a purpose built balance there can be up to 19 balanced components in addition to the main balance which measures the loads on that component The model loads are tested to the

    Original URL path: http://www.ara.co.uk/fr/services/aerodynamique-experimentale/transonic-wind-tunnel-testing/civil-aircraft/stability-and-control/ (2016-02-17)
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  • Rear Fuselage Performance » Aircraft Research Association
    Careers Vacancies New Page fr New Page fr New Page fr New Page fr Benefits Apprentices Personal Experiences Graduates Industrial Placements Work Experience Contact Rear Fuselage Performance Aircraft Research Association Services Aérodynamique Expérimentale Transonic Wind Tunnel Testing Civil Aircraft Rear Fuselage Performance The nature of the airflow over the rear fuselage and empennage the horizontal and vertical tail surfaces of a civil aircraft is fundamental to the effective operation of the tail control surfaces and has a significant affect on overall aerodynamic efficiency It is difficult to predict the airflow of the rear fuselage without using wind tunnels due to complexity Why ARA Two alternative twin sting support designs are available at ARA the Standard Twin Sting Rig STSR and the Enhanced Twin Sting Rig ETSR The STSR is the original twin sting support system and is extensively used for the measurement of empennage characteristics because it is free from central sting interference Together with panel loads on the horizontal tailplane vertical stabilisers rudders and elevators for models which can be easily split both aerodynamically and mechanically the empennage can be mounted on an internal balance The STSR booms incorporate balances to enable some of the overall forces or moments acting on the model to be monitored for safety However for close coupled aircraft layouts such as many modern executive jets which incorporate engines mounted to the rear fuselage aft of the wings there is strong mutual aerodynamic interaction between the complex fuselage shape wing nacelles empennage and central support sting and therefore the model fuselage can be neither aerodynamically or mechanically split in a sensible fashion for testing on the STSR For these cases ARA developed an Enhanced Twin Sting Rig which can measure the aerodynamic characteristics of different rear fuselage designs empennages and rear fuselage nacelle installations together with the determination of central sting corrections The basic concept of the ETSR is that the foces and moments acting on the whole model are accurately measured by two six component balances one mounted in each of the twin stings To ensure the highest possible data quality the whole model or ETSR system is calibrated as an assembly prior to testing in the TWT Uniquely both of our support systems can move in yaw as well as in pitch which enables both lateral and longitudinal stability and control to be investigated during a test In addition the horizontal separation of the support booms can be adjusted to our customer s specification A Typical Test When testing rear fuselage performance models are supported via the wings with a twin sting arrangement rather than via a central single sting This is because a twin sting allows for a more representative fuselage shape to be modelled The focus of the test is on the performance of the rear of the aircraft meaning that the support booms have no influence During a typical test the aerodynamic loads on the rear fuselage can be measured by creating a small gap between the rear fuselage and

    Original URL path: http://www.ara.co.uk/fr/services/aerodynamique-experimentale/transonic-wind-tunnel-testing/civil-aircraft/rear-fuselage-performance/ (2016-02-17)
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  • Installed Propulsion Performance » Aircraft Research Association
    Registration Careers Vacancies New Page fr New Page fr New Page fr New Page fr Benefits Apprentices Personal Experiences Graduates Industrial Placements Work Experience Contact Installed Propulsion Performance Aircraft Research Association Services Aérodynamique Expérimentale Transonic Wind Tunnel Testing Civil Aircraft Installed Propulsion Performance A typical civil aircraft is most often propelled by propeller engines or jet engines More advanced engines such as open rotors jet engines with fan blades on the outside are under active development Whatever means the aircraft uses to propel itself will have significant effects on the airflow around the aircraft The challenge aircraft designers face is to prevent these effects from disrupting the aerodynamic efficiency or stability and control of the aircraft Propeller Simulation We have a world leading capability in propeller testing for half span models built on decades of pioneering work into balance hub and blade design as well as telemetry and data acquisition We offer both single propeller twin propeller and contra prop configurations The propellers are powered by air motors driven by a high pressure air supply Our advanced health monitoring system for the air motors and propeller blades is very successful in detecting potential problems before they occur providing significant advances in reliability and productivity Our one stop service includes the manufacture of the rotary balances followed by calibration in our Balance Calibration Laboratory as well as fine tuning the balancing of propeller assemblies in our Propeller Test Cell Jet Simulation ARA has been a pioneer in jet propulsion testing since TPS units turbine powered simulators driven by high pressure air were first developed over 40 years ago TPS units allow a high fidelity simulation of inlet conditions and bypass flow through a jet engine model Our one stop service includes the design and manufacture of the engine models followed by

    Original URL path: http://www.ara.co.uk/fr/services/aerodynamique-experimentale/transonic-wind-tunnel-testing/civil-aircraft/installed-propulsion-performance/ (2016-02-17)
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  • Isolated Propulsion Performance » Aircraft Research Association
    and Manufacture Mécanique des Fluides Numérique CFD Software Code Development CFD Software Code Application Applied Aerodynamics Integrated CFD Wind Tunnel Weapons and Weapon Bay Analysis Wing Design Process Aerodynamic Research Innovation et technologie Clean Sky Project Strain Gauge Balance Developments Pressure Sensitive Paint Model Deformation Measurement New Page fr Media Centre Image Library Video Gallery Document Downloads Newsletter Registration Careers Vacancies New Page fr New Page fr New Page fr New Page fr Benefits Apprentices Personal Experiences Graduates Industrial Placements Work Experience Contact Isolated Propulsion Performance Aircraft Research Association Services Aérodynamique Expérimentale Transonic Wind Tunnel Testing Civil Aircraft Isolated Propulsion Performance Large Scale Isolated Propeller Testing The Acoustic Liner The continuous drive for reductions in fuel burn for commercial aircraft means that the development of open rotor propulsion systems will be one of the most important areas of research now and in the long term The acoustic signatures of such systems and the acquisition of noise data is a very important part of these development programs ARA has an unique capability within Europe for noise measurements on large scale propeller and open rotor systems at speeds up to Mach 0 8 An acoustic liner is mounted in the Transonic Wind Tunnel working section providing sufficiently anechoic conditions to allow the measurement of acoustic tones on open rotor configurations Acoustic measurements are made using either a microphone traversing rig or fixed microphone arrays Open rotor systems of up to 1 metre diameter are tested mounted on 440 kW induction or electric motors The motors can be configured to drive either single or contra rotating open rotors Each rotor is mounted on a strain gauge balance to measure thrust torque and off axis loads Near and far field acoustic characteristics are measured using high quality microphones along with rotor performance and pressure

    Original URL path: http://www.ara.co.uk/fr/services/aerodynamique-experimentale/transonic-wind-tunnel-testing/civil-aircraft/isolated-propulsion-performance/ (2016-02-17)
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  • Military Aircraft, UAV’s and Missiles » Aircraft Research Association
    Control Intake Performance Installed Store Loads Isolated Store Loads Data Quality and Repeatability Productivity Customer Facilities Other Test Facilities Balance Calibration Laboratory Mach Simulation Tank Propeller Test Cell Small Scale Transonic Tunnel 2 Dimensional Tunnel Large Scale Thrust Measuring Rig New Page fr Conception et Fabrication CAD Design Services Precision Model Manufacture Inspection Services Finite Element Analysis Strain Gauge Balance Design and Manufacture Mécanique des Fluides Numérique CFD Software Code Development CFD Software Code Application Applied Aerodynamics Integrated CFD Wind Tunnel Weapons and Weapon Bay Analysis Wing Design Process Aerodynamic Research Innovation et technologie Clean Sky Project Strain Gauge Balance Developments Pressure Sensitive Paint Model Deformation Measurement New Page fr Media Centre Image Library Video Gallery Document Downloads Newsletter Registration Careers Vacancies New Page fr New Page fr New Page fr New Page fr Benefits Apprentices Personal Experiences Graduates Industrial Placements Work Experience Contact Military Aircraft UAV s and Missiles Aircraft Research Association Services Aérodynamique Expérimentale Transonic Wind Tunnel Testing Military Aircraft UAV s and Missiles Simulating the operational envelope of a combat aircraft and the deployment of a missile requires the development of a comprehensive range of wind tunnel test techniques Here the accurate simulation of the air vehicle s aerodynamic performance can be the critical difference between its mission s success and failure ARA has worked on some of the World s most demanding military aircraft and weapons programs and received awards from our customers in recognition for the notable contributions we have made to the success of these projects The aircraft that ARA has worked on include Tornado Harrier T 50 Typhoon and F 35 We have worked closely with the World s leading aircraft and weapon manufacturers on the development and integration of stores such as Brimstone Amraam and Meteor As the operational envelope of unmanned

    Original URL path: http://www.ara.co.uk/fr/services/aerodynamique-experimentale/transonic-wind-tunnel-testing/military-aircraft-uavs-and-missiles/ (2016-02-17)
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  • Store Separation » Aircraft Research Association
    separation testing is vital before a new store such as a missile or a fuel tank can be used in service on an aircraft These tests are used to ensure that a store on release is able to clear the parent aircraft safely without endangering the aircraft or pilot ARA has developed the Two Sting Rig TSR system which we believe to be the most accurate system to meet this requirement in the world with its unique store release simulation capability Using this positional accuracies can be measured to within 0 05 inches or 1 25mm The TSR system achieves this level of accuracy through monitoring the relative positions of lights mounted in known positions on the store and aircraft using a calibrated camera system Using this system allows ARA to add value in the area of store release testing due to efficient and accurate testing especially when compared with the expensive alternative of flight testing The TSR has been used at ARA since 1979 and has been used to support store integration programs in a wide variety of production and developmental aircraft including Stormshadow Raptor and Brimstone integration on Tornado and Harrier in the UK International customers include Saab Scania with Gripen KAI with the T 50 and Lockheed Martin with the F 16 Why ARA If a customer works with ARA they can take advantage of Stores positioned in location and attitude with superb accuracy levels Pitch Yaw 0 15 Y Z 0 15mm Store movement is continuous allowing for excellent productivity for example up to 15 trajectories up to 30 grids grid survey test technique and up to 20 traverses freestream traversing technique per hour is possible Decades of experience testing a wide range of stores and aircraft Efficient test campaigns all set up data validated before

    Original URL path: http://www.ara.co.uk/fr/services/aerodynamique-experimentale/transonic-wind-tunnel-testing/military-aircraft-uavs-and-missiles/store-separation/ (2016-02-17)
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  • Stability and Control » Aircraft Research Association
    fr New Page fr New Page fr New Page fr Benefits Apprentices Personal Experiences Graduates Industrial Placements Work Experience Contact Stability and Control Aircraft Research Association Services Aérodynamique Expérimentale Transonic Wind Tunnel Testing Military Aircraft UAV s and Missiles Stability and Control Most modern fighter aircraft have been designed with some degree of inherent aerodynamic instability requiring close control by fly by wire computers Therefore it is vitally important that the stability and control aerodynamics of the aircraft are fully understood throughout the flight envelope at all speeds attitudes and payload combinations as these data form the basis of the flight control software systems It is important to acquire stability and control data for a large number of store payloads to provide sufficient data for aircraft flight control systems The safety of the aircraft and crew are therefore dependent on the fidelity of the aerodynamic data base For military aircraft control panel loads determination is also important since control panel loadings are affected by the payload carried on the aircraft more especially by external stores Loads on various control panels may be derived either directly by use of panel balances or by measuring pressures on the upper and lower surfaces of the panel and integrating these data Why ARA ARA has many years of experience in the measurement of stability and control aerodynamic data for a wide variety of military aircraft throughout the global market including Tornado and Typhoon This has enabled highly accurate stability and control data acquisition methods to be developed coupled with excellent productivity Individual control panel loads may also be measured simultaneously with the overall stability and control loads ARA has extensive experience in the measurement of payload forces and moments for both individual stores and multiple stores on racks launchers etc This experience has enabled

    Original URL path: http://www.ara.co.uk/fr/services/aerodynamique-experimentale/transonic-wind-tunnel-testing/military-aircraft-uavs-and-missiles/stability-and-control/ (2016-02-17)
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  • Intake Performance » Aircraft Research Association
    Aircraft Research Association Services Aérodynamique Expérimentale Transonic Wind Tunnel Testing Military Aircraft UAV s and Missiles Intake Performance The intakes of the vehicle i e aircraft cruise missile etc deliver the air to the engines It is important that the air flowing into any engine is well behaved so that the engines operate efficiently and reliably with minimal maintenance The intakes must retain optimal functionality throughout the operational envelope whatever the speed or attitude of the vehicle Why ARA ARA has extensive experience in the design and manufacture of bespoke ejectors and engine face rakes together with appropriate intake models and support structures We also have an on site intake duct calibration facility the Mach Simulation Tank It can be used to calibrate model engine nacelle duct intake thrust and discharge coefficients over the range of pressure ratios experienced in both the Transonic Wind Tunnel and a quiescent environment This facility may also be used to check the operation of engine face rakes Due to the dynamic nature of air flow a high speed data acquisition system is also vital ARA has a bespoke system for the acquisition of high speed steady state and dynamic data in real time during testing Coupled with real time data reduction techniques this system provides immediate access to the results of pressure recovery and distortion using the ARA data monitoring system A Typical Test An intake test involves the design and manufacture of a model of an appropriate section of the vehicle to be tested for an aircraft this might be the forward fuselage only whilst for a missile it may consist of most of the fuselage and the wings in the appropriate deployed position Integrated into this model is an ejector powered by a supply of high pressure air which induces the required

    Original URL path: http://www.ara.co.uk/fr/services/aerodynamique-experimentale/transonic-wind-tunnel-testing/military-aircraft-uavs-and-missiles/intake-performance/ (2016-02-17)
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