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A variable speed rigid rotor blade

A technology of rotor blades and variable speed, which is applied in the directions of rotorcraft, motor vehicles, aircraft, etc., can solve the problems of non-rigid rotor blade design, and achieves the effect of compact structure, easy implementation, and increased pendulum stiffness.

Active Publication Date: 2022-04-05
NO 60 RES INST OF GENERAL STAFF DEPT PLA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] In the existing blade design technology, the blade design is mainly for propeller aircraft and conventional helicopters, and there is no special design for the rigid rotor blades of long-endurance unmanned helicopters

Method used

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  • A variable speed rigid rotor blade
  • A variable speed rigid rotor blade
  • A variable speed rigid rotor blade

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Embodiment Construction

[0026] The present invention can be better understood from the following examples.

[0027] The structures, proportions, sizes, etc. shown in the accompanying drawings of the description are only used to match the content disclosed in the description, for those who are familiar with the technology to understand and read, and are not used to limit the conditions for the implementation of the present invention, so there is no Technically, any modification of structure, change of proportional relationship or adjustment of size shall still fall within the scope of the technical content disclosed in the present invention without affecting the functions and objectives of the present invention. within the range that can be covered. At the same time, terms such as "upper", "lower", "front", "rear", and "middle" quoted in this specification are only for the convenience of description, and are not used to limit the scope of the present invention. , the change or adjustment of its relat...

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Abstract

The invention discloses a variable-speed rigid rotor blade, which comprises a variable-section split winding girder belt, a variable-section trailing edge strip, a split bushing assembly, a PMI rigid foam core and a composite material skin; The variable cross-section split-wound girder belt is laid at the leading edge along the span of the blade, and the cross-sectional area is linearly distributed and gradually decreases; at the root of the blade, the variable-section split-wound girder belt is divided into two parts, the upper and lower airfoils. and respectively wound on the split bushing assembly; the variable-section trailing edge strip is laid between the trailing edge of the blade and the composite material skin along the span of the blade, and the cross-sectional area is linearly distributed along the span of the blade; The PMI rigid foam filler is placed between the variable-section split-wound girder belt and the variable-section trailing edge strip. The variable speed rigid rotor blade of the present invention can meet the dynamic rigidity requirement of the blade, can realize the integral connection of the blade and the hub, and reduce the resistance of the hub.

Description

technical field [0001] The invention belongs to the technical field of helicopter blades, in particular to a variable speed rigid rotor blade. Background technique [0002] Helicopters have the advantages of vertical take-off and landing, fixed-point hovering, etc. In recent years, unmanned helicopters have been greatly developed and applied in the military field. Compared with fixed-wing UAVs, unmanned helicopters have the advantage of vertical take-off and landing on ships, so they have great application prospects. my country has a vast territory, long coastline, and numerous islands. It has urgent needs for reconnaissance inspections, long-distance transportation, and anti-submarine operations. This puts high demands on the endurance of unmanned helicopters. [0003] In order to improve the endurance of the helicopter, a variable-speed long-endurance helicopter has appeared. This kind of helicopter can adjust the rotor speed in real time according to the flight parameter...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C27/473B64C27/467
CPCB64C27/473B64C27/467B64C2027/4736B64C2027/4733
Inventor 邵松焦志文刘士明应旭成贺敏锐
Owner NO 60 RES INST OF GENERAL STAFF DEPT PLA
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