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Segmented Piezoelectric Rudder Wing for Micro Aircraft

A kind of aircraft, segmented technology, applied in aircraft parts, aircraft control, transportation and packaging, etc., can solve the problems of unreachable deflection angle, reduced deflection angle of rudder wing, and failure to see, etc., to achieve reliable and simple connection Effect

Inactive Publication Date: 2016-09-21
NANJING UNIV OF SCI & TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, the maximum deflection angle of the integral piezoelectric rudder wing is limited by the size of the piezoelectric driver. When the structural size decreases, the deflection angle of the rudder wing will also decrease, which may not meet the deflection angle requirements.
However, no similar technology research report has been seen in China.

Method used

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  • Segmented Piezoelectric Rudder Wing for Micro Aircraft

Examples

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Embodiment

[0019] A segmented piezoelectric rudder for a micro aircraft, comprising a fixed bracket 1, a flap 2, a piezoelectric bimorph driver and a drive shaft 5, and a copper base 4 is sandwiched between two piezoelectric ceramic sheets 3 to form a piezoelectric bimorph The driver, the fixing bracket 1 connects the rudder system with the aircraft, and provides a fixed and operating platform for the piezoelectric bimorph driver and the flap 2. There is a cavity in the fixing bracket 1, and the piezoelectric bimorph driver is arranged in the cavity and fixed. There is a fixed fulcrum at the rear end of the bracket 1, and the flap is connected through the rotating shaft 6 to form a hinge structure. The fixed end of the piezoelectric bimorph driver is fixed in the cavity, and the free end is fixed with a drive shaft 5, which is movably matched with the chute on the flap through the driver shaft 5, and the thickness of the cavity is greater than that of the piezoelectric bimorph driver, so ...

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Abstract

The invention discloses a segmented piezoelectric rudder wing for a tiny aircraft, which comprises a fixed bracket, a flap, a piezoelectric bimorph driver and a drive shaft. There is a cavity in the fixed bracket, and the piezoelectric bimorph driver is arranged in the cavity. The fixed end is fixed in the cavity, and the free end is fixedly connected with the drive shaft. The thickness of the cavity is greater than that of the piezoelectric bimorph driver. The driving shaft is placed in the chute, and the opening width of the chute is the same as the diameter of the driving shaft, wherein, the fixed bracket, the flap and the driving shaft are all made of insulating materials; A sufficient deflection angle can be guaranteed.

Description

technical field [0001] The invention belongs to the technical field of aircraft rudder wing control, in particular to a segmented piezoelectric rudder wing of a micro aircraft. Background technique [0002] The flight control of the fixed-wing micro-aircraft must rely on the rudder structure. The traditional rudder structure of the aircraft is powered by electric, hydraulic or pneumatic. These power sources can be very well applied to various types of aircraft with relatively large sizes. For micro aircraft, due to the complex structure of hydraulic and pneumatic steering gear and many parts, it is very difficult to miniaturize it to the required size, and it cannot be applied in the field of micro aircraft. At present, micro-motors are mainly used to drive the rudder structure on fixed-wing micro-vehicles. However, micro-motors have disadvantages such as high price, large quality, and a single cylindrical shape. Therefore, foreign scholars considered applying piezoelectr...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C13/00
Inventor 周玉华周长省陈雄周俊杨庆辉姜丽辉闫爱天
Owner NANJING UNIV OF SCI & TECH
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