small drone body

A technology for small unmanned aerial vehicles and fuselage, applied in the direction of fuselage frame, toy aircraft, toys, etc., can solve the problems of high cost, increased weight, high strength, etc., to prevent local instability, reduce cost, and reduce aircraft weight and cost effects

Active Publication Date: 2011-11-23
CHENGDU AIRCRAFT INDUSTRY GROUP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

There are also disadvantages of excessive residual strength, increased weight and high cost

Method used

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Experimental program
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Embodiment Construction

[0019] Fig. 1 describes the main structure of the whole small unmanned aerial vehicle fuselage. The entire fuselage structure can include five frames, four

[0022] The stringers are of fiberglass laminate construction. The section of the longitudinal beam is T-shaped, and the edge strips on it are connected with the skin and the mouth cover.

[0023] The right piece skin 2 of non-metallic material is a co-cured sandwich structure of aramid paper honeycomb core and glass fiber panel. folder

[0025] For reducing weight, each mouth cover 3,5,6,7 is the same as the skin, and is a sandwich structure. The edge of the cover is the connecting part, same as

[0026] The nose cover 1 and the umbrella cabin 13 are integral shell structures of glass fiber laminates. Frontmost machine head cover 1 is used for structure

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Abstract

The fuselage of a small unmanned aerial vehicle related to the present invention comprises a fuselage box-shaped shell composed of a frame beam as a skeleton and a skin attached thereon, and the frames and beams constituting the fuselage skeleton are made of glass fiber laminated boards. composition. The frame is a frame with ribs on the front and back of the web, and the section is I-shaped; the beam is a longitudinal member with ribs, a reinforcing rib in the middle, and a T-shaped section; The body skin is a non-metallic honeycomb core/glass fiber panel co-cured sandwich panel. The present invention adopts the glass fiber composite material cured at room temperature with lower cost and the main surface part adopts light non-metallic honeycomb core and glass fiber panel to co-cure the interlayer, and its reduced weight is more than 30% lighter than that of aluminum alloy material. The cost can be reduced by more than 60%. It not only greatly reduces the weight and cost of the aircraft, but also has higher specific stiffness and strength.

Description

Technical Field of Small UAV Fuselage [0001] The present invention relates to a low-cost, lightweight small UAV fuselage. technical background The unmanned aerial vehicle fuselage is that each parts such as wing, landing gear, engine are connected as a whole, and load fuel oil and various equipment important components. The fuselage of the UAV not only bears the bending moment, shear force, torque generated by the wing surface and the thrust generated by the engine, but also bears The inertial force of various loads and the impact load generated by the launch device, landing gear, recovery umbrella, etc., is the most stress-bearing condition of the aircraft. for complex components. And not only to meet the requirements of strength, stiffness, toughness and other mechanical properties, but also to meet the requirements of weight, service life Life, manufacturability, maintainability, low cost and other aspects of the requirements. The fuselages of existing small UAVs...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C1/06A63H27/18
Inventor 李景虎
Owner CHENGDU AIRCRAFT INDUSTRY GROUP
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