Connecting structure for unmanned aerial vehicle body and wing

A technology for connecting structures and unmanned aerial vehicles, applied in the direction of fuselage, aircraft parts, toy planes, etc., can solve the problems of difficult repair and replacement, complex manufacturing process, low fatigue resistance, etc., to achieve strong replaceability and manufacturing. The effect of simple process and large production batch

A technology for connecting structures and unmanned aerial vehicles, applied in the direction of fuselage, aircraft parts, toy planes, etc., can solve the problems of difficult repair and replacement, complex manufacturing process, low fatigue resistance, etc., to achieve strong replaceability and manufacturing. The effect of simple process and large production batch

CN100497088CInactive Publication Date: 2009-06-10BEIHANG UNIV
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  • Connecting structure for unmanned aerial vehicle body and wing
  • Connecting structure for unmanned aerial vehicle body and wing
  • Connecting structure for unmanned aerial vehicle body and wing

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Embodiment Construction

[0026] The present invention will be further described in detail below in conjunction with the accompanying drawings.

[0027] A connection structure between a UAV fuselage and a wing of the present invention is realized by connecting a pair of front and rear joints of the wing with a pair of front and rear joints on the bottom plate of the fuselage fuel tank, such as figure 1 As shown, the front joint 1 of the wing is connected to the front joint 2 of the fuselage, and the rear joint 3 of the wing is connected to the rear joint 4 of the fuselage. The enlarged diagram of the connection structure of parts A and B is shown in figure 2 shown, combined with Figure 4 Structural diagram of wing front joint 1 and Figure 5 The structural diagram of the front joint 2 of the fuselage shows that the front joint 1 of the wing is connected to the upper surface of the wing through the side ear 16, and the front part is riveted to the wing box wall plate through a number of screw holes i...

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Abstract

The present invention discloses a connection structure of an airframe-airfoil of an unmanned aerial vehicle, which is realized by the connection of a pair of front and back joints of the airfoil and a pair of front and back joints at the oil box soleplate of the airframe that is the front joint of the airfoil is connected with the front joint of the airframe by bolts, and the back joint of the airfoil is connected with the back joint of the airframe by bolts. The airfoil and the airframe are linked just by four pairs of joints and four connection pieces, and the force transmission of the connection pieces is reasonable, which reduces the connection of joint parts and the concentration of stress; a majority of load is discharged during flying, which improves the anti-fatigue performance. The present invention has the characteristics of small size, good flexibility and large production batch. The structure can improve the rigidity of the joints to ensure the firm connection of the airframe and the airfoil and the high efficiency of the structure, and the structure belongs to the external connection, which has strong changeability and meets the requirement of combat readiness.

Description

technical field [0001] The invention belongs to the field of aviation machinery, and in particular relates to a connection structure between a fuselage and a wing of an unmanned aerial vehicle. Background technique [0002] At present, UAVs have been widely used in many fields such as campaign and strategic reconnaissance, surveillance, target positioning, target damage assessment, electronic countermeasures, and communication relay. Due to the advantages of UAVs such as low cost, good penetration capabilities and their outstanding performance in practice, the troops also urgently need to use various UAVs with excellent performance. Therefore, safety, reliability, economy and use requirements are the biggest challenges for UAV design. The connection between the fuselage and the wing bears a large load, which is a key fatigue component related to the flight safety of the aircraft. On the one hand, the loads it bears come from various mass forces (including the mass forces of...

Claims

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Application Information

Patent Timeline
10 Jun 2009
Publication
CN100497088C
IPC
B64C1/00; A63H27/18
Inventors
李倧伟; θŒƒζ›ΌεŽ