Shunting jet-propelled aircraft

By designing the turbine engine thrust of a split-jet aircraft, the safety and lifespan issues of rotor blades have been resolved, enabling efficient and flexible vertical takeoff and landing and air control, suitable for various aircraft applications.

CN120902944APending Publication Date: 2025-11-07中物(广东)数据信息技术有限公司 +1
0 Cites 0 Cited by

Patent Information

Application Number
CN202511287176.4
Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Filing Date
2025-09-10
Publication Date
2025-11-07

AI Technical Summary

Technical Problem

Existing low-altitude aircraft rotor blades pose safety hazards and have short lifespans when rotating at high speeds, and their reliance on runways for takeoff and landing makes them inflexible.

Method used

It adopts a split-jet design with high thrust efficiency of turbine engine, including jet mechanism, split nacelle, flight control nacelle, jet control mechanism and retractable tail fin. The turbine engine is not exposed, and efficient thrust control and flexible flight are achieved through split nacelle and jet control mechanism.

Benefits of technology

Turbine engines have high thrust, long lifespan, and good safety. Aircraft with them have a compact structure, low air resistance, can take off and land vertically, have unique control methods, are highly flexible, and are suitable for various combinations.

✦ Generated by Eureka AI based on patent content.
Patent Text Reader

Abstract

The invention relates to the field of aircrafts, in particular to a split-flow jet aircraft. The device comprises an air injection mechanism, a shunting cabin, a flight control cabin, an air injection regulation and control mechanism and a telescopic empennage, the air injection mechanism injects air from top to bottom; the shunting cabin is arranged at the bottom of the air injection mechanism, the top of the shunting cabin is provided with an air inlet channel, and the periphery of the shunting cabin is provided with a plurality of uniformly-distributed shunting ports; the flight control cabin is arranged at the bottom of the shunting cabin; a plurality of groups of air injection regulation and control mechanisms are uniformly arranged on the periphery of the shunting cabin, introduce air injected from the shunting port, control the air circulation range and inject the air downwards; and multiple groups of telescopic empennages are uniformly arranged around the shunting cabin. The turbine engine used in the invention is high in thrust efficiency, good in effect, safer and long in service life.
Need to check novelty before this filing date? Find Prior Art