Stamped drone fuselage structure with quick-release wings

Abstract

This invention relates to a stamped unmanned aerial vehicle (UAV) fuselage structure with quick-release wing functionality, comprising a fuselage module, at least one wing segment module, at least one outer skin, and at least one quick-release fastener assembly. The fuselage module is composed of multiple frame units integrally formed and stamped; the wing segment module is detachably assembled with or with the fuselage module, and is also composed of multiple frame units integrally formed and stamped; the outer skin covers the outer side of the fuselage module or the wing segment module, and is integrally formed and stamped; the quick-release fastener assembly is disposed at the mating point between the fuselage module and the wing segment module, or at the mating point between two adjacent wing segment modules, and, after being fastened, prevents the fuselage module from detaching from the wing segment module or the two adjacent wing segment modules. In one embodiment, the stamped UAV fuselage structure with quick-release wing functionality further includes a carbon fiber reinforcing tube assembly. This assembly extends longitudinally through the fuselage module and the wing segment module, and through the interlocking relationship of the sleeve and connector, combined with quick-release fasteners, achieves rapid assembly and secure reinforcement. This improves the assembly efficiency, disassembly convenience, transportation convenience, structural strength, lightweight effect, and mass production stability of large UAVs.

Claims

1. A stamped unmanned aerial vehicle (UAV) fuselage structure with quick-release wing functionality, comprising: A fuselage module, which is composed of a plurality of frame units integrally formed, cut, and stamped; at least one wing segment module, which is detachably assembled with the fuselage module or with each other, and which is also composed of a plurality of frame units integrally formed, cut, and stamped; at least one outer skin, which is applied to the outer side of the fuselage module or the wing segment modules, and which is integrally formed, cut, and stamped; and at least one quick-release fastener assembly, which is disposed at the mating point between the fuselage module and the wing segment modules, or at the mating point between two adjacent wing segment modules; wherein the quick-release fastener assembly is used to prevent the fuselage module from disengaging from the wing segment modules or the two adjacent wing segment modules after being fastened.

2. The stamped unmanned aerial vehicle airframe structure with quick-release wing function as described in claim 1 further includes a carbon fiber reinforcing tube assembly that extends longitudinally through the fuselage module and the wing segment modules.

3. The stamped UAV fuselage structure with quick-release wing function as described in claim 2, wherein the carbon fiber reinforcing tube assembly further includes at least one sleeve and at least one insertion tube, the sleeves being respectively disposed in the fuselage module and the wing segment modules, and when the quick-release assembly is fastened, the two ends of the insertion tube are pre-inserted into the sleeves and tightly engaged, and after the quick-release assembly is fastened, the fuselage module is restricted from disengaging from the wing segment modules or the two adjacent wing segment modules.

4. The stamped unmanned aerial vehicle body structure with quick-release wing function as described in claim 3, wherein the connectors and sleeves are tightly fitted, interference-fitted, or provided with elastic bushings, anti-slip layers, adhesive layers, wear-resistant linings, or combinations thereof.

5. The stamped unmanned aerial vehicle (UAV) fuselage structure with quick-detach wing function as described in claim 1, wherein the number of wing segment modules is multiple, and includes a first wing segment module, a second wing segment module and a third wing segment module, wherein the first wing segment module is detachably connected to the fuselage module, the second wing segment module is detachably connected to the first wing segment module, and the third wing segment module is detachably connected to the second wing segment module.

6. The stamped unmanned aerial vehicle body structure with quick-release wing function as described in claim 1, wherein the quick-release fastener assembly includes a first fastener seat, a second fastener seat and a fastener arm, and the fastener arm is pivotable relative to the first fastener seat and fastened to the second fastener seat to restrict the fuselage module from disengaging from the wing segment modules or the adjacent two wing segment modules.

7. The stamped unmanned aerial vehicle airframe structure with quick-release wing function as described in claim 1, wherein the frame units are cut and stamped with a folded edge structure.

8. The stamped unmanned aerial vehicle airframe structure with quick-release wing function as described in claim 1, wherein the frame units are cut and stamped with a reinforcing rib.

9. The stamped unmanned aerial vehicle airframe structure with quick-release wing function as described in claim 1, wherein the frame units are cut and stamped with a plurality of weight-reduction openings.

10. A stamped unmanned aerial vehicle (UAV) airframe structure with quick-release wings as described in claim 1, wherein the outer skins are applied to the outside of the fuselage module or the wing segment modules by riveting, welding, bonding, fastening, or a combination thereof.

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