Manned aerial vehicle and unmanned aerial vehicle combined system

A combined system and unmanned aerial vehicle technology, applied in the field of aircraft design, can solve the problem that it is difficult to obtain the balance between the performance of the carrier aircraft and the performance of the unmanned aerial vehicle, low versatility, adaptability and extended use ability, adaptability and versatility It can improve the adaptability and flexibility of use, reduce the cost of replacement and transformation, and improve the cruising speed.

Active Publication Date: 2021-04-06
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] Existing manned / drone combinations require aircraft At the cost of a certain loss of aerodynamic drag or reduction of flight performance, it is difficult to achieve a balance between the performance of the carrier aircraft itself and the performance of the UAV
In addition, unmanned aerial vehicles and manned aircraft must be designed synchronously, and the versatility, adaptability, and expansion capabilities of both are low, and it is difficult to solve the control problems caused by the large differences in the aerodynamic layout of different configurations
Manned aircraft are mostly used as dedicated unmanned aerial vehicles, and their own adaptability and versatility are not strong

Method used

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  • Manned aerial vehicle and unmanned aerial vehicle combined system

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Embodiment 1

[0026] The combined layout of the manned machine + UAV constructed by the present invention has the advantages of flexible configuration, mature scheme, less constraints on manned machine, less performance loss of manned machine / drone, and less difficulty in aerodynamic conversion of different configurations.

[0027] Such as Figure 1-2 As shown, the present application provides a combined system of manned aircraft and unmanned aerial vehicle, including manned aircraft (1) and unmanned aerial vehicle (2).

[0028] The manned aircraft adopts a normal layout, with a built-in single (or twin) engine placed inside the fuselage (or hoisted as follows), a retractable canard, and a single vertical tail; the wing adopts a high-lift wing with a low Reynolds number type. Control rudder surfaces are set at the trailing edges of the front and rear wings, and a nacelle is set in the middle of the wing to store the landing gear and the front coupler of the UAV.

[0029] The UAV adopts a ...

Embodiment 2

[0032] One embodiment of the present invention is a combined attack system of a manned attack aircraft and an unmanned aerial vehicle. Specifically, it includes manned aircraft (1) and unmanned aerial vehicles (2). The manned aircraft adopts a normal layout with retractable canards, and a nacelle is set in the middle of the wing to store the landing gear and the front coupler of the drone. The UAV adopts straight and retractable wings, and the outer section of the wing can be retracted inward to the inner wing section; the horizontal tail can be folded and retracted / extended and released. The two-point connection method between the nose of the UAV and the nacelle of the wing of the manned aircraft, and the tip of the wing of the UAV and the tip of the flat tail of the manned aircraft. The two connection points can realize synchronous connection / separation; the connection point also has a data transmission device. ability.

[0033] The manned aircraft has a length of 12m, a w...

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Abstract

The invention provides a manned aerial vehicle and unmanned aerial vehicle combined system which comprises a manned vehicle (1), a first externally-hung unmanned aerial vehicle (2), a second externally-hung unmanned aerial vehicle (3), a front coupler (4) and a wingtip coupler (5), nacelles are arranged in the middles of wings on the two sides of the manned vehicle (1), and the nacelles on the two sides are provided with manned vehicle front couplers (4); wing tips on two sides of a horizontal tail of the manned aircraft (1) are respectively provided with a manned wing tip coupler; an unmanned aerial vehicle front coupler of the first externally-hung unmanned aerial vehicle (2) and an unmanned aerial vehicle front coupler of the second externally-hung unmanned aerial vehicle (3) are connected with manned vehicle front couplers of nacelles on the two sides of the manned vehicle (1) respectively; the unmanned aerial vehicle wingtip coupler of the first externally-hung unmanned aerial vehicle (2) and the unmanned aerial vehicle wingtip coupler of the second externally-hung unmanned aerial vehicle (3) are connected with the manned vehicle wingtip couplers on the two sides of the manned vehicle (1) respectively.

Description

technical field [0001] This application relates to aircraft design, in particular to a combined system of a manned machine and an unmanned aerial vehicle. Background technique [0002] The combination of manned machine and unmanned aerial vehicle is the direction of future aviation development. The current manned / unmanned aerial vehicle combination usually adopts two methods: the unmanned aerial vehicle mounted under the wing of the manned aerial vehicle and the unmanned aerial vehicle mounted in the compartment inside the fuselage. The former is constrained by factors such as the mounting capacity of the hanging point under the wing and the size of the surrounding structure of the hanging point, and has high requirements for the weight, geometric size, and layout of the UAV; The requirements for factors such as the size of the body cabin are relatively high. Both forms do not have the ability to mount large / medium-sized drones. [0003] In order to meet the requirements ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C37/00B64D5/00B64C39/12
CPCB64C37/00B64D5/00B64C39/12
Inventor 党育辉向文俊谭蓉蓉
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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