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Small-size retractable multi-wheel and multi-support undercarriage

A technology of aircraft landing gear and wheel frame, which is applied in wheel type, chassis and other directions, can solve the problems of complex hydraulic system structure, unsuitable for small unmanned aerial vehicles, heavy weight, etc., to reduce structural complexity, eliminate adverse effects, reduce The effect of weight

Inactive Publication Date: 2013-06-05
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0010] Generally, the hydraulic system is used for retracting and retracting the landing gear of aircraft. However, due to the complex structure and heavy weight of the hydraulic system, it is not suitable for small UAVs. A lighter and simpler retractable power must be used.

Method used

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  • Small-size retractable multi-wheel and multi-support undercarriage
  • Small-size retractable multi-wheel and multi-support undercarriage
  • Small-size retractable multi-wheel and multi-support undercarriage

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Embodiment Construction

[0030] The present invention is mainly realized through rational design, assembly and debugging of the load-bearing pillar of the landing gear, retractable linkage and locking mechanism, machine wheel and brake, and pneumatic control system.

[0031] The technical scheme of concrete implementation of the present invention is illustrated below in conjunction with accompanying drawing (taking the landing gear on the right side as an example, the left side is mirror-symmetrical with it about the fuselage longitudinal symmetry plane):

[0032] An embodiment of the landing gear of the present invention is figure 1 and figure 2 As shown, the landing gear is respectively connected with, for example, four fuselage reinforcement frames 1 through, for example, seven mounting parts 10, wherein only one first mounting joint 13 positioned at the upper part is fixed on the foremost fuselage reinforcement frame 1, and the remaining three Each fuselage reinforcement frame 1 is fixed with a ...

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Abstract

The invention provides an airplane undercarriage. The undercarriage comprises a plurality of airplane wheel-wheel carrier units and a retraction driving component, wherein the plurality of airplane wheel-wheel carrier units are arranged one after another; each of the plurality of airplane wheel-wheel carrier units comprises an airplane wheel component and a wheel carrier for supporting and retracting the airplane wheel components; and the retraction driving component is linked with each airplane wheel-wheel carrier unit and used for driving the plurality of airplane wheel-wheel carrier units to retract / release the airplane wheel components. The supports of the small-size retractable multi-wheel and multi-support undercarriage are retracted by using a simple linkage device, and the small-size retractable multi-wheel and multi-support undercarriage can be retracted in the limited internal space of the vehicle body of a small-size unmanned aerial vehicle and has enough intensity, rigidity, high practicability and reliability.

Description

[0001] This application is a divisional application of Chinese Patent Application No. 200910078388.6. technical field [0002] The invention relates to the design of a small retractable multi-wheel multi-pillar landing gear, which belongs to the field of structural design of aviation aircraft, and is suitable for unmanned scaling verification machines for small unmanned aerial vehicles and large aircrafts with large load requirements. Wait. Background technique [0003] The present invention is mainly applied to small unmanned aerial vehicles with low landing gear height and high take-off weight, especially unmanned scale verification aircraft of aircraft such as large transport aircraft. [0004] With the rapid development of electronic technology, computer technology, material technology and high-precision manufacturing technology, various microelectronic devices, light-strength composite materials and small propulsion machinery with large thrust-to-weight ratio (piston en...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C25/34B64C25/10
Inventor 王立波万志强杨超
Owner BEIHANG UNIV