Aligning system and control method of three-wing-surface tilt aircraft

By integrating a water immersion sensor, attitude sensor and air pressure monitoring system on the aircraft, and utilizing the buoyancy of the righting airbag to automatically right the rocker-shaped aircraft, the problem of capsizing on water is solved, and environmental adaptability and safety are improved.

CN120621677APending Publication Date: 2025-09-12BEIJING ZERO CREATION ZHONGCHENG TECH CO LTD
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Patent Information

Application Number
CN202410834411.4
Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Filing Date
2024-06-26
Publication Date
2025-09-12

AI Technical Summary

Technical Problem

Amphibious aircraft with a cantilever configuration are easily disturbed by wind or choppy water surface and may capsize when landing or mooring on water, and existing technology cannot effectively realize automatic righting.

Method used

The self-centering system, which consists of a water immersion sensor, an attitude sensor, an air pressure monitoring sensor, and a flight control integrated module, uses the buoyancy of the self-centering airbag to generate torque on the fuselage for automatic self-centering, and combines attitude and air pressure monitoring to achieve precise control.

Benefits of technology

The automatic tilting and righting of the cantilevered aircraft in complex environments has been achieved, which improves environmental adaptability and safety and reduces the risk of equipment damage and mission failure.

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Abstract

The invention relates to the technical field of an aligning system and a control method of a three-airfoil seesaw aircraft, and discloses an aligning system of a three-airfoil seesaw aircraft, which comprises a fuselage, a front wing assembly, a middle wing assembly and a rear wing assembly, a water immersion sensor, an attitude sensor, an air pressure monitoring sensor, an instantaneous inflation and deflation valve and a flight control integrated module are embedded in the fuselage; the detection end of the water immersion sensor extends to the front face of the fuselage, the flight control integrated module is located on the rear side of the water immersion sensor, the output ends of the instantaneous inflation and deflation valves are connected with return air bags, the air pressure monitoring sensor is located on the left side of the flight control integrated module, and the attitude sensor is located on the left side of the air pressure monitoring sensor. The return system and the control method of the three-airfoil seesaw aircraft have the advantages of automatic return during overturning and the like, and the problem that when an amphibious aircraft of a seesaw structure lands or parks on the water, overturning is easily caused by interference of wind or fluctuating water surfaces is solved.
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