Integrated control system for aircraft with V-shaped empennage

A control system and aircraft technology, applied in the field of control systems, can solve the problems of inconvenient control, complex control system structure, large cabin space, etc., and achieve the effects of weight reduction, simple control system, and small size

Active Publication Date: 2012-11-07
YUNEEC TECH CO LTD +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The technical problem to be solved by the present invention is to provide a control system that is easy to operate, easy to use and maintain, and saves cabin space in order to overcome the disadvantages of the prior art V-tail aircraft, such as complex structure, inconvenient control, and large cabin space. Integrated V-tail aircraft control system

Method used

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  • Integrated control system for aircraft with V-shaped empennage
  • Integrated control system for aircraft with V-shaped empennage
  • Integrated control system for aircraft with V-shaped empennage

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Embodiment Construction

[0041] The preferred embodiments of the present invention are given below in conjunction with the accompanying drawings to describe the technical solution of the present invention in detail.

[0042] Such as Figure 2 to Figure 5 As shown, the integrated V-tail aircraft control system provided by the present invention includes a cross section that is connected to the body of the aircraft in rotation. Type of shaft 1, used to fix the The bracket 13 of the rotating shaft 1; two handles 2 respectively movable at the two ends of the rotating shaft 1 and used to drive the rotating shaft 1 to rotate along the axis O-O synchronously. At the same time, the two handles 2 can also be left, Swing right. Wherein, when the two handles 2 rotate along the axis O-O or swing left and right in the plane where the cross section of the rotating shaft 1 is located, they can act synchronously.

[0043] Carry out lifting or direction deflection control in order to control the V-shaped tail 8 of...

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PUM

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Abstract

The invention discloses an integrated control system for an aircraft with a V-shaped empennage. The integrated control system comprises a rotary shaft, two handles, an oscillating shaft, an upper rocker, a lower rocker and an aileron transmission shaft, the rotary shaft is rotationally connected onto a body of the aircraft, the two handles are used for synchronously driving the rotary shaft to rotate axially and can synchronously oscillate in a plane with the cross section of the rotary shaft, the oscillating shaft is arranged on the rotary shaft eccentrically, movably and penetratingly, the upper rocker is fixedly arranged on the top of the oscillating shaft, the lower rocker is fixedly arranged at the bottom of the oscillating shaft, and the aileron transmission shaft is movably connected with an aileron system of the aircraft and used for obliquely controlling ailerons of the aircraft. A hand control system and a hybrid control system of the aircraft are integrated in the integrated control system with the handles creatively, accordingly, the control system of the aircraft is simple and is small in size, precious occupied space in a cabin of the aircraft is saved, and service and maintenance properties of the control system are improved.

Description

technical field [0001] The invention relates to an aircraft control system, in particular to an integrated V-tail aircraft control system. Background technique [0002] At present, the V-tail control system of foreign traditional light aircraft mainly consists of two independent handle control systems and a mixed control central control system. Such as figure 1 As shown, during operation, the mixing control central control system 20 is usually manipulated through the handle control system 10, and then the mixing control central control system 20 is connected with the pedal control system 30 to realize the elevator of the V-shaped tail of the aircraft. and rudder for lifting and left and right yaw control. This method is to transmit the lifting operation and the left and right deviation operations to the mixed control central control system 20 respectively, and then the mixed control central control system 20 realizes the aircraft lift and steering control. [0003] For th...

Claims

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Application Information

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IPC IPC(8): B64D31/04
Inventor 田瑜江文彦
Owner YUNEEC TECH CO LTD
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