Norman S. Currey's Aircraft Landing Gear Design: Principles and Practices (AIAA PDF

By Norman S. Currey

This can be the single publication to be had this day that covers army and advertisement airplane touchdown apparatus layout. it's a finished textual content that might lead scholars and engineers from the preliminary thoughts of touchdown apparatus layout via ultimate element layout. The e-book presents an important hyperlink in touchdown equipment layout know-how from historic practices to fashionable layout tendencies, and it considers the mandatory airfield interface with touchdown apparatus layout. The textual content is sponsored up through calculations, requisites, references, operating examples.

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Extra resources for Aircraft Landing Gear Design: Principles and Practices (AIAA Education Series)

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A . , >,=6 o. r,h A) 35 stops at average i of 10 ft/s 2 e,g,h Source: AS 227. aSea level power-off stalling speed at design landing weight and configuration. bOne change of friction materials is permissible in meeting the 66 stops. For other than friction materials, the assembly shall withstand the 65 stops without failure or impairment of operation. CAt the most critical combination of takeoff weight and anticipated optimum V~ speed. dAt anticipated takeoff weight. Rotorcraft speed at brake application shall be determined by )analysis.

MIL-W-5013 also calls for the installation of thermal-sensitive pressurerelease devices (fuse plugs), such as depicted in Fig. 5, with the requirement that they function whenever the bead ledge temperature reaches 400°F. They are placed in the wheel 120 deg apart to prevent tire or wheel explosion due to tire and/or brake overheating. To prevent tire damage or failure, insure that the wheel bead seat temperature from brake heat does not exceed 350°F for normal energy and overload energy. A means must be provided to prevent water from entering the wheel bearings.

Clearances between the tire and adjacent parts of the aircraft shall be based upon a 3% growth in tire section width and height from the MIL-T-5041 dimensions. 5% increase in section height should be allowed for centrifugal growth. 4 of ARP 1493. Wheels are designed in accordance with MIL-W-5013. The aircraft manufacturer is responsible for calculating the maximum static and dynamic loads on the wheels, which must be less than their rated loads. REQUIREMENTS 53 FUSlll VENT ~FA~ SPLIT Fig. 5 Wheel details.

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Aircraft Landing Gear Design: Principles and Practices (AIAA Education Series) by Norman S. Currey


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