Miniature double-flapping-wing aircraft capable of realizing autonomous stability augmentation control and control moment generation method thereof

A flapping wing aircraft and control method technology, applied in aircraft, attitude control, control/adjustment system, etc., can solve the problems of low control rudder efficiency, easy loss of lift of aircraft, easy change of center of gravity position, etc.

Active Publication Date: 2021-02-02
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0009] The present invention aims at the problems of stability enhancement control and yaw control of the existing miniature double flapping wing aircraft, and at the same time, in order to solve the problems of low control rudder efficiency of the aircraft, easy loss of lift

Method used

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  • Miniature double-flapping-wing aircraft capable of realizing autonomous stability augmentation control and control moment generation method thereof
  • Miniature double-flapping-wing aircraft capable of realizing autonomous stability augmentation control and control moment generation method thereof
  • Miniature double-flapping-wing aircraft capable of realizing autonomous stability augmentation control and control moment generation method thereof

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Embodiment Construction

[0048] The present invention will be further described in detail with reference to the accompanying drawings and embodiments.

[0049] Such as figure 1 As shown, the present invention is a miniature double flapping-wing aircraft capable of autonomous stability-increasing control, including an intermediate connection structure 1 , a flapping-wing system 2 and a stability-increasing control system 3 . Arrow points forward.

[0050] Such as figure 2 As shown, the intermediate connection structure 1 is a three-dimensional structure, and two holes are opened at the front and rear ends of the upper part, which are used to fix the two sets of flapping mechanisms 21 at the front and rear, so as to combine the two flapping mechanisms 21 into a whole.

[0051] Such as figure 1 As shown, there are two sets of the flapping wing system 2, and each set includes a flapping mechanism 21 and a flapping wing 22.

[0052] Such as figure 1 As shown, the flapping mechanism 21 includes a holl...

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Abstract

The invention discloses a miniature double-flapping-wing aircraft capable of autonomous stability augmentation control and a three-degree-of-freedom control moment generation method thereof. The miniature double-flapping-wing aircraft specifically comprises two identical driving systems, a lifting force system and a control system, the two driving systems are connected through a middle connectingstructure, and the driving systems drive the lifting force system to generate a lifting force; the control system changes the lift system to generate control torque. The aircraft can efficiently generate pitching, rolling and yawing three-axis control torque, estimates aircraft state information through a complementary filtering and Kalman filtering algorithm, and performs autonomous stability augmentation control. The aircraft has the autonomous stability augmentation flight capacity, the yawing performance is improved emphatically, rolling and yawing are controlled only by changing the tension degree of the wing films, gravity center changes unfavorable for control are avoided, and lift force losses in the stability augmentation control process are reduced.

Description

technical field [0001] The invention relates to the field of micro-aircraft, in particular to a miniature double-flapping-wing aircraft capable of autonomous stability enhancement control and a method for generating control torque thereof. Background technique [0002] With the continuous innovation of aircraft design concepts and the great progress of microelectronics technology at the end of the last century, micro air vehicles were proposed and developed rapidly. With the characteristics of small size, light weight and strong maneuverability, micro air vehicles are suitable for reconnaissance, exploration and rescue assistance in complex environments, and have broad application prospects. As an important branch of micro-aircraft, the bionic flapping-wing micro-aircraft gradually began to appear with the development of bionics design. The flapping-wing micro-aircraft relies on the reciprocating flapping of the flapping wings to generate lift, and generates control torque ...

Claims

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Application Information

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IPC IPC(8): B64C33/02G05D1/08
CPCB64C33/02G05D1/0816Y02T50/40
Inventor 张艳来赵国栋吴江浩
Owner BEIHANG UNIV
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