Small-sized foldable multi-wheel multi-column support type landing gear

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

Inactive Publication Date: 2009-07-15
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0009] 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-sized foldable multi-wheel multi-column support type landing gear
  • Small-sized foldable multi-wheel multi-column support type landing gear
  • Small-sized foldable multi-wheel multi-column support type landing gear

Examples

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Embodiment Construction

[0029] 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.

[0030] 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):

[0031] 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 aircraft landing frame comprising a plurality of machine wheel-wheel frame units and an unfolding and folding drive subassembly, wherein the machine wheel-wheel frame units are arrayed forwards and backwards, each machine wheel-wheel frame unit comprises a machine wheel subassembly and a wheel frame which is used for supporting, unfolding and folding the machine wheel subassembly, and the unfolding and folding drive subassembly is linked with each machine wheel-wheel frame unit and is used for driving the machine wheel-wheel frame units to carry out the folding/unfolding operation of the machine wheel subassembly. In the miniature retractable landing frame with multiple wheels and supporting posts, the supporting posts are folded and unfolded by adopting a simple linking device, and the landing frame can be contained into an internal limited space of a machine body of a miniature unmanned machine and has sufficient strength and rigidity and better practicability and reliability.

Description

technical field [0001] 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 [0002] 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. [0003] 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 engines, The performance of turbojet engine and electric motor) has been greatly improved. Small UAVs ar...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C25/22B64C25/10
Inventor 王立波万志强杨超
Owner BEIHANG UNIV
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