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combined ducted aircraft

A technology of aircraft and ducting, applied in the field of aircraft, to achieve the effect of high control efficiency and use efficiency

Active Publication Date: 2018-01-23
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0005] The invention provides a combined ducted aircraft, which solves the problems of balanced anti-torque, unitary design of a single element and multi-component combination, and satisfies the flight conditions of a single ducted aircraft and any multi-ducted combined aircraft, and has aerodynamic efficiency, High operating efficiency and use efficiency, vertical take-off and landing, hybrid power, economy, safety, practicality and other advantages

Method used

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Embodiment Construction

[0020] The present invention will be further described below in conjunction with accompanying drawing.

[0021] Combined ducted aircraft is composed of several primitive devices. When there is only one elementary unit, it is a single ducted rotorcraft; its structure is as follows: figure 1 and figure 2 As shown, the duct body 3 is included, and the duct body 3 is provided with a power unit, a structural support member 2, a rotor 4, a deflector 1 and a deflector angle of attack control device, and the power unit is a rotor 4 and a deflector angle of attack control device. Corner controls provide power. The structural support 2 is an internal hollow structure, and power lines and control lines pass through the structural support 2 . The outer wall of the duct body 3 is provided with an expansion interface 5 .

[0022] deflector angle of attack control device such as image 3 As shown, it includes a central control ring 6 and a steering gear 7, and the steering gear 7 contro...

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Abstract

The invention provides a combined duct aircraft which comprises a plurality of element devices.Each element device comprises a duct body.A power device, a structure supporting member, a rotor wing, a flow guide plate and a flow guide plate attack angle control device are arranged in each duct body, wherein the power device provides power for the rotor wing and the flow guide plate attach angle control device, the flow guide plate attack angle control device comprises a center control ring and a steering engine, and the steering engine controls the change of the flow guide plate attack angle through the center control ring.An expanding connector is formed in the outer wall of each duct body and comprises a structure supporting member connector.The adjacent element devices are connected through the structure supporting members and the expanding connectors.The combined dust aircraft can be disassembled into the smallest single body element for carrying and transporting and a single duct aircraft to execute small-task-load flight, can also be fast combined into the multi-duct aircraft suitable for various task requirements, and has the advantages of achieving vertical take-off and landing, generating hybrid power, and being economical, safe, practical and the like.

Description

technical field [0001] The invention relates to the field of aircraft, in particular to an aircraft with combined ducts. Background technique [0002] Ducted aircraft use rotors (or propellers or fans, hereinafter collectively referred to as rotors) installed in ducts as lift systems. If a single rotor is used, then the counter torque produced by the rotor must be balanced by installing a balanced counter torque system ; If dual rotors are used, the aerodynamic efficiency and energy utilization efficiency of the ducted rotor lift system will be reduced, and the duct depth will be lengthened to meet the installation space of the dual rotors. Therefore, there are fewer ducted aircrafts with dual-rotor configurations, and the main ways to balance the anti-torque for single-rotor ducted aircrafts are: 1) Use double-number ducts (double ducts, four ducts, six ducts) 2) Install deflectors or trim pieces in the duct, and use the action of rotor downwash to generate aerodynamic tor...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C27/12B64C27/20B64C27/32
CPCB64C27/12B64C27/20B64C27/32
Inventor 朱清华肖升兴张昊招启军徐起
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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