Undercarriage control mechanism of small aircraft

A small aircraft and control mechanism technology, applied in landing gear, aircraft parts, chassis, etc., can solve the problems of increased occupied space, damage to hydraulic drive equipment, etc., and achieve the effect of reducing installation space, increasing stability, and strong functionality

Active Publication Date: 2020-06-02
JIANGSU TIANYI AIRPORT SPECIAL EQUIP CO LTD
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  • Abstract
  • Description
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  • Application Information

AI Technical Summary

Problems solved by technology

In the landing gear used by common small aircraft, there is usually a front main wheel at the front end of the aircraft, and a set of rear main wheels on each side at the rear of the aircraft. In order to make the aircraft have better taxiing stability, the rear main wheels are added It is a more favorable choice to set the rear main wheel, but after adding the rear main wheel, it is necessary to install a lifting drive device matching the rear main wheel, which increases the occupied space; usually the landing gear is driven by hydraulic drive equipment (such as hydraulic cylinders) Lifting, during the landing process of the aircraft, the landing gear will transmit the impact force to the connected hydraulic equipment, and the instantaneous impact force will easily damage the hydraulic drive equipment

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  • Undercarriage control mechanism of small aircraft
  • Undercarriage control mechanism of small aircraft
  • Undercarriage control mechanism of small aircraft

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Embodiment Construction

[0019] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0020] see Figure 1 to Figure 4 , the present invention provides a technical solution: a landing gear control mechanism for a small aircraft, comprising a drive box 1, a first lifting bracket 2 and a second lifting bracket 201, combined with figure 1 with figure 2 As shown, both ends of the drive box 1 are fixedly connected with a side support 3 by bolts, the middle part of the side support 3 is provided with a notch 301, and the outer side wall of the side...

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Abstract

The invention relates to the technical field of undercarriages, especially to an undercarriage control mechanism of a small aircraft. The mechanism comprises a driving box, a first lifting bracket anda second lifting bracket, and the two sides of the driving box are provided with side seats which are respectively connected with the first lifting bracket and the second lifting bracket. The undercarriage control mechanism has the beneficial effects that the driving box is connected with the aircraft wheels through the first lifting bracket and the second lifting bracket arranged on the two sides respectively, and compared with the structure that only one aircraft wheel is arranged in a transmission mode, the aircraft has better stability in the sliding process; lifting control over the first lifting bracket and the second lifting bracket can be completed through one set of driving equipment, and the installation space of the driving equipment is reduced while the stability of an airplane in the sliding process is improved.

Description

technical field [0001] The invention relates to the technical field of landing gear, in particular to a landing gear control mechanism of a small aircraft. Background technique [0002] Landing gear is an accessory device used to support the aircraft and move on the ground when the lower part of the aircraft is used for takeoff and landing or ground taxiing. In the landing gear used by common small aircraft, there is usually a front main wheel at the front end of the aircraft, and a set of rear main wheels on each side at the rear of the aircraft. In order to make the aircraft have better taxiing stability, the rear main wheels are added It is a more favorable choice to set the rear main wheel, but after adding the rear main wheel, it is necessary to install a lifting drive device matching the rear main wheel, which increases the occupied space; usually the landing gear is driven by hydraulic drive equipment (such as hydraulic cylinders) Lifting, during the landing process ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C25/34B64C25/58B64C25/22
CPCB64C25/22B64C25/34B64C25/58B64C2025/345
Inventor 陈少峰
Owner JIANGSU TIANYI AIRPORT SPECIAL EQUIP CO LTD
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