Aircraft landing gear

a technology for landing gear and aircraft, applied in the direction of wheel arrangement, braking arrangement of aircraft, transportation and packaging, etc., can solve the problem of carbon disk wear and tear

Inactive Publication Date: 2019-11-21
AIRBUS OPERATIONS LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

This solution efficiently dissipates energy through heat or cavitation, effectively slowing aircraft rotation and ground speed, reducing wear and eliminating the need for large resistors or batteries, while providing a versatile braking system for both forward and reverse motion.

Problems solved by technology

The carbon disks are subject to wear, both during high-speed braking and especially during low-speed braking due to “surface plucking” of the brake disk surfaces.
However, such an arrangement would require a large (and heavy) resistor to be connected to the generator so that the electrical energy generated from the kinetic energy can be converted into heat energy and dissipated.

Method used

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  • Aircraft landing gear
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Experimental program
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Effect test

first embodiment

[0052]FIG. 1 shows a diagrammatic view of an e-taxi system architecture 100, as part of an aircraft landing gear, according to the invention. The e-taxi architecture 100 may be part of an otherwise known landing gear arrangement, such as described in WO 2015 / 025131. The e-taxi system 100 comprises a wheel actuator 101 connected by an electrical connection 102 to the e-taxi power electronics 103, including a motor (not shown) that can also act as a generator. The power electronics 103 are connected by an electrical connection 104 to a mono tube steam generator 105.

[0053]Also shown is an aircraft water supply 110 connected by a water supply line 111a to a pump 112 and from the pump 112 by water supply line 111b to the mono tube steam generator 105. Also shown is the exhaustion of steam from the mono tube steam generator at arrow 113. Also shown is an electrical connection 106 between the e-taxi power electronics 103 and the pump 112 so that the power electronics 103 can provide power ...

third embodiment

[0069]FIG. 3 shows a side view of a cavitation braking device 300 according to the invention. The cavitation braking device 300 may be part of an otherwise known landing gear arrangement, such as described in WO 2015 / 025131. The cavitation device 300 comprises an inner first part 311 fixedly attached to a wheel axle 310. Hence, the first part does not rotate. The cavitation braking device also comprises an outer second part 320 mounted inside a wheel hub (not shown). The second part therefore rotates (shown by arrow 321) with the wheel so that it rotates around the first part 311.

[0070]The first part 311 is in the form of a cone with the slanted surface 312 being at an angle of approximately 30 degrees to the axle. This slanted surface 312 is a first cavitation surface 312 and comprises a number of blind holes 313 extending from the surface.

[0071]The second part 320 also has a cavitation surface, the second cavitation surface 322. This surface is parallel to but slightly spaced from...

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Abstract

An aircraft landing gear is disclosed having a wheel rotatably mounted on an axle, a first gearing element that rotates with the wheel, a second gearing element configured to mesh with the first gearing element such that rotation of the first gearing element causes rotation of the second gearing element, wherein the second gearing element is connected to a generator, such that rotation of the second gearing element causes the generator to generate electrical energy, further comprising a heat dissipation device connected to the generator wherein the heat dissipation device comprises an electrical heating element connectable to the generator to receive generated electrical energy and convert it to heat energy, and a fluid receptacle adjacent the heating element, such that fluid in the receptacle can be heated.

Description

CROSS RELATED APPLICATIONS[0001]This application is a Divisional of U.S. patent application Ser. No. 15 / 386,116, filed Dec. 21, 2016, now pending, which claims priority from Great Britain Patent Application No. 1522695.4, filed Dec. 22, 2015, the entire contents of each of which are hereby incorporated by reference.BACKGROUND OF THE INVENTION[0002]The present disclosure relates to aircraft landing gear.[0003]The present invention concerns aircraft landing gear. More particularly, but not exclusively, this invention concerns an aircraft landing gear comprising an axle and a wheel rotatably mounted on the axle.[0004]The invention also concerns an aircraft and a method of braking.[0005]Many commercial passenger aircraft use carbon brakes, comprising a number of “carbon-carbon” composite disks that can be pushed together by hydraulic actuators, in order slow relative rotation of the disks. The carbon disks are subject to wear, both during high-speed braking and especially during low-spe...

Claims

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Application Information

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Patent Type & AuthorityApplications(United States)
IPC IPC(8): B64C25/40B64C25/34B64C25/42
CPCB64C25/42Y02T50/823B64C25/405B64C25/34B60L7/00B60L2200/10Y02T50/80B60L7/02
InventorWILSON, FRASER
OwnerAIRBUS OPERATIONS LTD