A compartmentalized unmanned helicopter

The design of the unmanned helicopter, featuring modular cargo compartment components and a tandem rotor configuration, resolves the conflict between center of gravity balance and space utilization, thereby improving flight stability and ease of maintenance, and enhancing the equipment's safety and endurance.

CN122078680APending Publication Date: 2026-05-26SHENZHEN TITANIUM TECHNOLOGY CO LTD +1
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
SHENZHEN TITANIUM TECHNOLOGY CO LTD
Filing Date
2026-04-22
Publication Date
2026-05-26

AI Technical Summary

Technical Problem

Existing unmanned helicopters have many limitations in terms of cargo hold layout, equipment configuration, structural design and functional coordination. The contradiction between center of gravity balance and space utilization is prominent, and the landing gear design cannot take into account both transportation and stability, which affects flight stability and safety.

Method used

The modular cargo hold components are arranged close to the center of gravity of the whole aircraft. Combined with the front-mounted fuel and rear-mounted power layout, the rotor system is optimized into a tandem twin-rotor configuration. It adopts wheeled landing gear and a partitioned isolation structure. The fuselage is equipped with heat insulation, sound insulation and electromagnetic shielding layers according to functional zones, and each system is laid out independently to avoid interference.

Benefits of technology

It improves flight stability and space utilization, reduces the risk of center of gravity shift, enhances maintenance convenience and equipment reliability, and improves takeoff and landing safety and endurance.

✦ Generated by Eureka AI based on patent content.

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Abstract

This application relates to a box-type unmanned helicopter, comprising: a fuselage, a modular cargo bay assembly fixedly mounted on the fuselage, the modular cargo bay assembly being located in the load mounting area in the middle of the fuselage and between the front rotor system and the rear rotor system; a front rotor system being located at the upper front of the fuselage; a rear rotor system being located at the upper rear of the fuselage; the front rotor system and the rear rotor system being symmetrically arranged at the front and rear ends of the top of the fuselage; a power system being located at the rear of the fuselage; the front rotor system and the rear rotor system being connected to the power system via a drive shaft; a fuel system being located at the front of the fuselage; and an avionics equipment bay being located at the front of the fuselage, within which an avionics system is fixedly installed. This invention improves flight stability and space utilization through structural layout optimization; the modular cargo bay assembly is positioned close to the overall design center of gravity and adapts to different mission payloads through a quick-positioning interface; the power system is located at the rear and equipped with an adaptable maintenance door; and the clear zoning of each system significantly improves maintenance efficiency and space utilization; the tandem dual rotor synchronous counter-rotation design improves lift, maneuverability, and wind resistance, and avoids airflow interference.
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