April 20, 2017

Download Airframe & Systems Tutorial - PPSC PDF

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The material most commonly used is high strength aluminium alloy, although a few highly stressed aircraft, particularly military types, use titanium spar webs. The attachment points between wing spar and fuselage centre section are often of titanium or steel alloy in large aircraft. Typical attachment point design is illustrated at Figure 1-15. Chapter 1 Page 23 © G LONGHURST 1999 All Rights Reserved Worldwide Airframe and Systems FIGURE 1-15 Typical Attachment Point Design Chapter 1 Page 24 © G LONGHURST 1999 All Rights Reserved Worldwide Airframe and Systems 43.

Individual pilot strengths will clearly vary and consequently airworthiness requirements stipulate specific load limits for conventional wheel type controls which should not have to be exceeded. To assist the pilot a variety of control balancing devices may be used, which reduce the aerodynamic force to be overcome. Chapter 1 Page 35 © G LONGHURST 1999 All Rights Reserved Worldwide Airframe and Systems Aerodynamic Balance 73. When a control surface is deflected the airflow acting over it will try to return the control to the neutral position.

The magnitude of the lift force generated by any control surface will vary directly as the square of the EAS. The pilot is required to provide the force to overcome the hinge moment and deflect the control surface (in a manual system). At all but the lowest airspeeds he or she could do with some form of assistance. This assistance is supplied in the form of control balance devices. 75. Control balancing is achieved either by reducing the hinge moment, or by setting up a force that acts against the hinge moment.

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