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Light-weight foldable reconnaissance/attack integrated unmanned aerial vehicle

A technology of unmanned aerial vehicles and folding mechanisms, applied in the field of unmanned aerial vehicles, can solve the problems of large volume, unusable unmanned aerial vehicle weight, and poor maneuverability, so as to reduce the speed of level flight, excellent maneuverability, and ensure the success rate Effect

Active Publication Date: 2018-03-09
哈尔滨模豆科技有限责任公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The purpose of the present invention is to provide a light-duty foldable unmanned aerial vehicle for inspection and combat, which can effectively solve the problems of the existing unmanned aerial vehicles in the prior art, which are expensive and difficult to maintain. In actual combat, it is difficult to quickly repair and then cannot be damaged again. The problem of putting into use and the existing drones are heavy, bulky, inconvenient to carry, and poor in maneuverability; the present invention provides a drone that can be quickly folded and unfolded, has low cost, simple structure and easy repair, and has excellent maneuverability. It can be used for military reconnaissance operations, fast and precise strike missions, and can also be used in civilian scientific research fields, such as atmospheric detection, surface surveying and mapping, etc.

Method used

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  • Light-weight foldable reconnaissance/attack integrated unmanned aerial vehicle
  • Light-weight foldable reconnaissance/attack integrated unmanned aerial vehicle
  • Light-weight foldable reconnaissance/attack integrated unmanned aerial vehicle

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specific Embodiment approach 1

[0038] Such as Figure 1-9 As shown, the light foldable unmanned aerial vehicle for reconnaissance and combat includes a fuselage, wings, a folding mechanism, a vertical tail 6, a reconnaissance platform 8 and a delivery mechanism 9. The fuselage includes a front fuselage 1, a rear fuselage Body 7, central wing box, wing main girder, fuselage connection box and tail connection box; Described wing comprises inner segment wing 2 and outer segment wing 3; Described wing is provided with left and right pairs, two The auxiliary wings are symmetrically arranged on both sides of the fuselage; the folding mechanism includes a wing folding mechanism 4 and a fuselage folding mechanism 5; the wing folding mechanism 4 is provided with two pairs; the front fuselage 1 passes through the The folding mechanism 5 is connected to the front end of the fuselage connection box, the rear end of the fuselage connection box is fixedly connected to the rear fuselage 7, and the rear end of the rear fus...

specific Embodiment approach 2

[0048] The aerodynamic layout and parameters of the light-duty foldable unmanned aerial vehicle for inspection and shooting of the present invention:

[0049] In order to set up the pilot cabin on the nose of the aircraft while ensuring a high enough thrust-to-weight ratio, the aircraft adopts a twin-engine power design. The aircraft wing is divided into inner and outer ends, using NACA4412 and NACA6412 airfoils respectively. The wingtip has a negative twist of 3 degrees relative to the wing root, the root-to-tip ratio is 1.778, the wingspan is 1332mm, the wing area is 0.337㎡, and the aspect ratio is 5.273. Straight leading edge, no upper reverse, no winglets, flat tail volume 0.531.

[0050] Most of the existing small unmanned reconnaissance aircraft adopt a single-engine upturn design with a large aspect ratio, and the wing area is not large. Due to the heavy weight of the carrier aircraft and various electronic equipment, it directly leads to a large wing load. Although su...

specific Embodiment approach 3

[0063] In the wing folding mechanism of the present invention, the lower surface of the wing adopts a metal spring hinge, which is used to connect the two sections of wings and provide the torque for springing back the wings to make them fold together. The upper surface uses a custom-made 65 manganese steel sheet to complete the fixation of the wing after rebounding. Specifically, the steel sheet extends from the inner section of the wing, and the outer diameter is the same as the outer diameter of the top of the connecting screw on the outer section of the wing. The extension hole, when the outer single wing rebounds upwards, the outer screw will automatically snap into the extension hole, and as the wing fully bounces back, the screw is locked with the outer edge of the extension hole. Such a mechanism can also be replaced by a structure similar to a clip, such as placing a horizontal sheet on the outer wing, leaving space above and below, and installing a semi-sawtooth-shape...

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Abstract

The invention relates to the field of unmanned aerial vehicles and especially relates to a light-weight foldable reconnaissance / attack integrated unmanned aerial vehicle, which includes a fuselage, wings, a folding mechanism, flat vertical tails, reconnaissance cloud deck, and a dispensing mechanism. The fuselage includes a front section, a rear section, a central wing box, wing main beams, wing connection boxes, and a tail connection box. Each wing includes an inner section and an outer section. The two wings are arranged respectively at the left and the right of the fuselage symmetrically. The folding mechanism includes two set of wing folding mechanisms and a fuselage folding mechanism. The reconnaissance / attack integrated unmanned aerial vehicle can be quickly folded and expanded, is low in cost, has simple and easy-to-repair structure, and has excellent maneuverability and certain dispensing load. The unmanned aerial vehicle is used for military reconnaissance and quick and accurate strike tasks, and also can be applied to civil and scientific researching fields, such as atmospheric sounding and topographic mapping, etc.

Description

technical field [0001] The invention relates to the field of unmanned aerial vehicles, in particular to a light-weight foldable integrated unmanned aerial vehicle for inspection and strike. Background technique [0002] UAVs are mostly fixed-wing aircraft, which take off by hand throw or take off in short distances. Most of them are electric, small in size and light in weight. Generally, metal materials and some advanced composite materials are used to reduce the structural weight, but their shapes are not regular enough, and most of them are larger than rotor drones, making it difficult to pack and carry. At the same time, the immediate repairability of most drones is poor, and the price is not cheap, generally above $5,000. UAVs in the prior art, such as a variable aspect ratio drone with a patent application number of CN201420040752.6, includes a fuselage, an outer wing, a middle wing, an empennage, and The power system also includes a connection mechanism between the o...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C39/02B64C3/56B64C1/06B64C1/30B64D47/08B64D1/12
CPCB64C1/068B64C1/30B64C3/56B64C39/02B64D1/12B64D47/08B64C2001/0063B64C2001/0072B64U2101/00
Inventor 吴春来
Owner 哈尔滨模豆科技有限责任公司
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