Why is titanium used for aircraft landing gear?

can u give me some reasons plz thanks

7 Answers

  • What gear did you see than on? It is very expensive to use in that application.

  • Titanium Landing Gear

  • Aluminum and Titaniom are nearly the same weight, but Titanium is much stronger per pound than Aluminum. The problems with Titanium however out weigh it's benefits with most companies. As stated before it is extremely expensive and rare. A fact learned by Lockheed when tehy were building the SR-71 Blackbird. They actually had to have the CIA forma front company to buy titanium from the soviet union in order to build planes to spy on the soviet union. Titanium is also ironically delicate when you try to form or weld with it. More lessons learned from the SR-71 production at Lockheed. Welds done during the summer were failing faster than welds done during the winter because the chlorine added to tap water in the summer was chemically weaking the welds. Lockheed eventually went to using distilled water year round to get rid of this problem. Of course now-a-days composites are used since they are light, strong and relatively ease to maunfacture and maintain. I hope this helps.

  • Titanium is not actually stronger than steel- the most common alloy, Ti 6Al 4V (6% aluminum, 4% vanadium) has a tensile strength of 130 ksi vs. about 270 for 4340M high strength steel. Steel has a density of 0.3 lb/cubic inch vs 0.16 lb/cu in for titanium; so the strength to weight ratio (specific strength) for Ti 6Al 4V is 130/.16= 812.5 ksi/lb/cu in while 4340M is 270/.3= 900 ksi/lb/cu in- a bit higher.

    Consequently, for most landing gear, the oleo (inner strut) and post (outer) are steel, not titanium. Steel is used where volume is limited. Titanium is used where ultimate strength is less critical as it has better crack resistance- often the truck beam (supporting the axles) and torsion links are titanium. Although expensive, titanium has excellent durability and corrosion resistance.

  • Titanium (Ti) is a lightweight, strong, corrosion-resistant element that can be alloyed with iron, aluminum, etc. The downside of its use is that it's more expensive than other alloys.

    It also has a much higher melting point (not that this makes a different in aviation use) of 1668 degrees Celcius (3034 degrees Farenheit).

  • high strength, low weight.

    It is stronger than most steel alloys, with about one third the weight.

  • high weight to strength ratio, low weight, absorbs impact better as well

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