阅读说明：本技术 一种垂直起降旋叶机螺旋桨可变复合叶片 (Variable composite blade of vertical take-off and landing rotary vane machine propeller ) 是由 陈泽园 于 2020-08-27 设计创作，主要内容包括：本发明涉及一种垂直起降旋叶机螺旋桨可变复合叶片,包括Z型支架,所述Z型支架两侧分别设置有双金属板,所述双金属板的表面设置有PET电热膜,所述Z型支架的内侧端部设置有电线,所述电线连接在PET电热膜上,其特征在于所述电线给所述PET电热膜通电加热来控制双金属板的变型量,设置在所述Z型支架两侧的双金属板相互间独立控制加热变型。通过加热PET电热膜,改变内板和外板的形状来满足不同条件下叶片的状态。通过该可变复合叶片,使飞机在任何环境下能够垂直起降,同时具有高速水平飞行能力,并且能够节省燃油。(The invention relates to a variable composite blade of a propeller of a vertical take-off and landing rotary vane machine, which comprises a Z-shaped support, wherein double metal plates are respectively arranged on two sides of the Z-shaped support, a PET (polyethylene terephthalate) electric heating film is arranged on the surface of each double metal plate, and an electric wire is arranged at the end part of the inner side of the Z-shaped support and is connected to the PET electric heating film. The shapes of the inner plate and the outer plate are changed to meet the state of the blade under different conditions by heating the PET electric heating film. By the variable composite blade, the airplane can take off and land vertically in any environment, has high-speed horizontal flight capability and can save fuel.)

1. The utility model provides a but vertical take-off and landing rotary vane machine screw variable composite blade, includes Z type support (1), Z type support (1) both sides are provided with bimetallic strip respectively, bimetallic strip's surface is provided with the PET electric heat membrane, the medial extremity of Z type support (1) is provided with electric wire (7), electric wire (7) are connected on the PET electric heat membrane, its characterized in that electric wire (7) give the deformation volume that PET electric heat membrane ohmic heating controlled bimetallic strip sets up the bimetallic strip of Z type support (1) both sides is independent control heating deformation each other.

2. The variable composite blade of a propeller of a vertical take-off and landing rotary vane machine according to claim 1, wherein the bimetal plate is fixedly arranged on the Z-shaped bracket (1) by bolts, and the bimetal plate comprises an inner plate (5) arranged at the inner side and an outer plate (9) arranged at the outer side.

3. The variable composite blade of a propeller of a vertical take-off and landing rotary vane machine according to claim 2, wherein the inner plate (5) and the outer plate (9) are made of japanese type ALBL-2 bimetal plates, wherein the inner plate (5) has a high expansion layer on the upper side, the outer plate (9) has a high expansion layer on the lower side, and the Z-shaped bracket (1) is made of a japanese type ALBL-2 bimetal plate high expansion metal aluminum nickel manganese iron alloy bracket with the same composition.

4. The variable composite blade of a propeller of a vertical take-off and landing rotary vane machine according to claim 2, wherein the Z-shaped bracket (1) is an aluminum alloy bracket with model 2024-T351, the inner plate (5) and the outer plate (9) comprise a high expansion layer and a low expansion layer, the high expansion layer comprises an aluminum alloy plate with model 2024-T351, the low expansion layer comprises an aluminum-silicon alloy plate with model AlSi70, the high expansion layer of the inner plate (5) is on top, and the high expansion layer of the outer plate (9) is on bottom.

5. The variable composite blade of a propeller of a vertical take-off and landing rotary vane machine according to any one of claims 1 to 4, wherein the PET electrothermal film is arranged on the high expansion layer of the bimetallic plate through high temperature resistant silica gel, and the temperature adjustment of the PET electrothermal film is realized through current adjustment, and the adjustment temperature range comprises 1 ℃ to 130 ℃.

6. The variable composite blade of the propeller of the vertical take-off and landing rotary vane machine according to claim 5, wherein a carbon fiber cloth (4) is arranged on the outer side of the PET electric heating film, the carbon fiber cloth (4) is arranged on the PET electric heating film through high-temperature resistant silica gel, and the carbon fiber cloth (4) is provided with one layer or a plurality of layers.

7. The variable composite blade of a propeller of a vertical take-off and landing rotary vane machine according to claim 1, wherein the electric wire (7) comprises a high temperature resistant silica gel wire, and the inner end of the Z-shaped bracket (1) is provided with a shaft end in which a Z-shaped bracket hole (6) for leading out the electric wire (7) is provided.

8. The variable composite blade for a propeller of a vertical take-off and landing rotary vane machine according to claim 7, wherein the shaft end is assembled on a main shaft (11) of an engine, and a blade angle adjustable pitch structure is arranged on the main shaft (11) of the engine.

9. The variable composite blade of a propeller of a vertical take-off and landing rotary vane machine according to claim 1, wherein the Z-shaped bracket (1) is provided with a mounting step (101) for attaching a metal plate.

Technical Field

The invention belongs to the technical field of aviation, and particularly relates to a variable composite blade of a vertical take-off and landing rotary vane machine propeller.

Background

The rotary vane can take off and land vertically and fly horizontally at high speed, and is mainly a worldwide problem for manufacturing airplane propeller blades (the shapes of the airplane propeller blades flying horizontally and the vertical take off and land propeller blades flying vertically are different). The variable composite blades of the propeller of the rotary vane machine are disclosed, and the vertical take-off and landing rotary vane machine in China becomes a reality. The application of the rotary vane machine in military affairs can lead the airplane to take off and land vertically in any environment, the high-speed horizontal flight is faster than that of a helicopter, and the fuel is saved. And the problem that the early warning machine and the anti-diving patrol machine take off and land on a small-sized aircraft carrier in China can be solved. The civil vertical take-off and landing flying automobile can be realized.

At present, the osprey propeller can be produced only in the United states all over the world, and the propeller of the osprey needs to be lifted vertically and fly horizontally, so that the lifting efficiency of the propeller of the osprey is low, the propeller of the osprey has a large diameter which is different from the shape of the horizontal flying propeller during horizontal flying, and the horizontal flying speed is slow due to the large diameter (slow rotating speed). The united states has also been developing and developing ways to shorten the length of propeller blades of rotary vane machines and to vary the propeller blades without success. However, only the united states can produce rotary vane machines worldwide, and rotary vane machines have not been developed in other countries for a while.

Disclosure of Invention

In order to solve the technical problems, the invention adopts the following scheme:

the utility model provides a but vertical take-off and landing vane spinner screw variable composite blade, includes Z type support, Z type support both sides are provided with bimetallic strip respectively, bimetallic strip's surface is provided with the PET electric heat membrane, the medial extremity of Z type support is provided with the electric wire, the connection of electric lines is on the PET electric heat membrane, its characterized in that the electric wire gives the deformation volume that PET electric heat membrane ohmic heating controlled bimetallic strip sets up the mutual independent control heating of bimetallic strip of Z type support both sides is variant.

The variable composite blade of the propeller of the vertical take-off and landing rotary vane machine is characterized in that the double metal plates are fixedly arranged on the Z-shaped support through bolts, and each double metal plate comprises an inner plate arranged on the inner side and an outer plate arranged on the outer side.

The variable composite blade of the propeller of the vertical lifting rotary vane machine is characterized in that the inner plate and the outer plate are made of Japanese Hitachi type ALBL-2 bimetallic plates, wherein the high expansion layer of the inner plate is arranged on the upper part, the high expansion layer of the outer plate is arranged on the lower part, and the Z-shaped support is made of an aluminum-nickel-manganese-iron alloy support.

The variable composite blade of the propeller of the vertical lifting rotary vane machine is characterized in that the Z-shaped bracket comprises an aluminum alloy bracket with the model number of 2024-T351, the inner plate and the outer plate comprise a high expansion layer and a low expansion layer, the high expansion layer comprises an aluminum alloy plate with the model number of 2024-T351, the low expansion layer comprises an aluminum-silicon alloy plate with the model number of AlSi70, the high expansion layer of the inner plate is arranged on the upper part, and the high expansion layer of the outer plate is arranged on the lower part.

The variable composite blade of the vertical take-off and landing rotary vane machine propeller is characterized in that the PET electric heating film is arranged on the high expansion layer of the bimetallic plate through high-temperature-resistant silica gel.

The variable composite blade of the propeller of the vertical take-off and landing rotary vane machine is characterized in that carbon fiber cloth is arranged on the outer side of the PET electric heating film, the carbon fiber cloth is arranged on the PET electric heating film through high-temperature-resistant silica gel, and one layer or multiple layers of the carbon fiber cloth are arranged.

The variable composite blade of the propeller of the vertical take-off and landing rotary vane machine is characterized in that the electric wire comprises a high-temperature-resistant silica gel wire, the end part of the inner side of the Z-shaped support is provided with a shaft end, and a Z-shaped support hole for leading out the electric wire is arranged in the shaft end.

The variable composite blade of the vertical take-off and landing rotary vane machine propeller is characterized in that the shaft end is assembled on a main shaft of an engine, and a blade angle adjustable variable pitch structure is arranged on the main shaft of the engine.

The variable composite blade of the propeller of the vertical take-off and landing rotary vane machine is characterized in that the Z-shaped bracket is provided with an installation step for connecting a metal plate.

The variable composite blade of the vertical take-off and landing rotary vane machine propeller has the following beneficial effects:

the shape of the inner plate and the outer plate is changed to meet the state of the blade under different flight conditions by electrifying and heating the PET electric heating film. When the engine is vertically lifted, the engine is vertical to the ground, the inner plate is bent into an arc shape, and the outer plate is horizontal, so that the engine rotates to generate a large lifting force. The inner plate is powered off to restore the inner plate to a plane state, the outer plate is powered off to change the outer plate to an arc state, the engine and the ground are leveled, and then the blade angle of the variable composite propeller is adjusted through the variable pitch structure which can adjust the blade angle on the main shaft of the engine, so that horizontal flight can be realized.

By the variable composite blade, the airplane can take off and land vertically in any environment, has high-speed horizontal flight capability and can save fuel.

Drawings

FIG. 1 is a schematic front view of the present invention;

FIG. 2 is a cross-sectional view A-A of FIG. 1;

FIG. 3 is a cross-sectional view taken along line B-B of FIG. 1;

FIG. 4 is a cross-sectional view taken along line C-C of FIG. 1

FIG. 5 is a cross-sectional view taken along line D-D in FIG. 1

FIG. 6 is a vertical take-off and landing effect diagram of the present invention;

fig. 7 is a horizontal flight effect diagram of the present invention.

In the figure: 1-Z-shaped stents; 101-mounting a step; 2-a first bolt; 3-a first PET electrothermal film; 4-carbon fiber cloth; 5-an inner plate; 6-Z-shaped bracket holes; 7-an electric wire; 8-a second PET electrothermal film; 9-an outer plate; 10-a second bolt; 11-the main shaft of the engine; 12-engine.

Detailed Description

The following detailed description of the embodiments of the present invention will be made with reference to the accompanying drawings, so that the technical solutions of the present invention can be understood and appreciated more easily.