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Case study on aero elasticity
- 2. Aero elasticity is the study of the interaction of inertial, structural and aerodynamic forces on aircraft, buildings, surface vehicles etc.
- 3. AERO ELASTICITY STATIC AEROELASTICITY DIVERGENCE CONTROL REVERSAL DYNAMIC AEROELASTICITY FLUTTER BUFFETING TRANSONIC
- 4. Elastic twist of the wing suddenly becoming theoretically infinite Phenomenon occurring only in wings with ailerons or other control surfaces, where control surfaces reverse their usual functionality DIVERGENCE: CONTROL REVERSAL: STATIC AEROELASTICITY
- 5. Dynamic instability DYNAMIC AEROELASTICITY A high-frequency instability Shock Waves
- 6. Boeing X-53 Active Aero elastic Wing
- 7. First flight -8 December 2006 Role -Technology Demonstrator National origin -United States Manufacturer -McDonnell Douglas Northrop Corporation
- 8. 1 Design and development
- 9. Integrates wing aerodynamics, controls, and structure to harness and control wing aero elastic twist at high speeds and dynamic pressures.
- 10. An aircraft maneuvers - deploying flight control surfaces into the airflow, which modify the lift of the surface they are attached to.
- 11. 1. Taking an existing F/A-18 airframe 2. Modified with a preproduction pre roll mod wing 3. Added an outboard leading edge flap drive system and an updated flight control computer
- 12. 2 Specifications General characteristics Crew: 1 Wingspan: 38 ft 5 in (11.71 m) Height: 15 ft 3 in (4.65 m) Max takeoff weight: 39,000 lb (17,690 kg) Power plant: 2 × General Electric F404-GE-400 low-bypass turbofan engines, 16,000 lbf (71 KN) thrust each Performance Maximum speed: 1,032 KN; 1,912 km/h (1,188 mph) Service ceiling: 50,000 ft (15,000 m)
- 14. Aero elastic twist can be controlled Enables the use of high aspect ratio, thin, swept wings Provide excellent high speed rolling performance No additional stiffness was added for static aero elastic issues Overall control authority is affected
Hinweis der Redaktion
- Aeroelasticity is the branch of physics and engineering that studies the interactions between the inertial, structural, and aerodynamic forces that occur when an elastic body is exposed to a fluid flow. In 1947, Arthur Collar defined aero elasticity as “the study of the mutual interaction that takes place within the triangle of the inertial, structural, and aerodynamic forces acting on structural members exposed to an airstream.”
- Now let us have a glance at the case study on Aero Elasticity. This is the application of study of aero elasticity in Aeronautics. That is Boeing X-53 Active Aero elastic Wing.
- The X-53 Active Aeroelastic Wing (AAW) development program is a completed research project that was jointly undertaken by the Air Force Research Laboratory (AFRL), Boeing Phantom Works and NASA's Dryden Flight Research Center.
- The concept uses high aspect ratio, thin, swept wings that are aero elastically deformed into shapes for optimum performance. This makes it possible to achieve the multi-point aerodynamic performance required for future fighter, bomber, and transport aircraft.
- The technology used here integrates wing aerodynamics, controls, and structure to control wing aero elastic twist at high speeds and dynamic pressures. AAW Technology employs wing aero elastic flexibility through use of multiple leading and trailing edge control surfaces activated by a digital flight control System
- For instance, the ailerons on the wings used to roll an aircraft work by increasing or decreasing the lift of the outer portion of one wing, while doing the opposite on the other wing. This imbalance in lift forces causes the aircraft to rotate around its longitudinal axis.
- To test the AAW theory, NASA and the USAF agreed to fund development of a single demonstrator, based on the F/A-18. Work started by taking an existing F/A-18 airframe modified with a preproduction pre roll mod wing, and added an outboard leading edge flap drive system and an updated flight control computer. Active aeroelastic wing control laws were developed to flex the wing and flight instrumentation was used to accurately measure the aeroelastic performance of the wing planform.
- The leading edge flap drive system was modified at McDonnell Douglas (now Boeing Phantom works) using a new outboard actuation unit developed by Moog. AAW flight control laws were programmed into a research flight control computer modified to include an independently actuated outboard leading edge control surfaces.
- By using multiple leading and trailing edge controls like “aerodynamic tabs”, subtle amounts of aeroelastic twist can be controlled. The concept enables the use of high aspect ratio, thin, swept wings that are aeroelastically deformed into shapes for optimum performance. It provides excellent high speed rolling But beyond this advantages there are some limitations. No additional stiffness was added for static aero elastic issues. The aeroelasticity still exists and is affecting the overall control authority