CN113548174A - Variable-configuration propeller structure and aircraft - Google Patents
Variable-configuration propeller structure and aircraft Download PDFInfo
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- CN113548174A CN113548174A CN202110843267.7A CN202110843267A CN113548174A CN 113548174 A CN113548174 A CN 113548174A CN 202110843267 A CN202110843267 A CN 202110843267A CN 113548174 A CN113548174 A CN 113548174A
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- propeller
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- 238000000034 method Methods 0.000 abstract description 2
- 230000008569 process Effects 0.000 abstract description 2
- 230000000694 effects Effects 0.000 description 4
- 229910000831 Steel Inorganic materials 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 239000010959 steel Substances 0.000 description 2
- 230000003044 adaptive effect Effects 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/16—Blades
- B64C11/20—Constructional features
- B64C11/28—Collapsible or foldable blades
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/02—Hub construction
- B64C11/14—Spinners
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a variable-configuration propeller structure and an aircraft, wherein the propeller structure comprises a hub and blades distributed around the hub, at least one blade is connected with the hub through a traction rope, and the diameter of the blade is adjusted through retraction and extension of the traction rope. The invention takes into account the propeller efficiency in the vertical take-off and landing stage and the cruise flight stage by changing the propeller configuration, namely, a large propeller disc configuration is adopted in the low-speed high-thrust stage, a small propeller disc configuration is adopted in the cruise low-thrust stage, and the propeller efficiency can be further improved by combining the use. The propeller configuration is dynamically controlled and adjusted by the control system in the flight process so as to match the thrust requirements of different flight modes and speeds, achieve the characteristics of high efficiency and high efficiency of the propeller system and reduce the flight power consumption.
Description
Technical Field
The invention relates to the technical field of propellers, in particular to a variable-configuration propeller structure and an aircraft.
Background
The propellers are widely applied to manned and unmanned power systems, from a large-scale manned transport plane to a small-scale fixed-wing aircraft and then to a consumer-grade quad-rotor unmanned plane, the application of the quad-rotor unmanned plane is everywhere visible, and the flight speed is from a subsonic transport plane to a quad-rotor unmanned plane with zero hovering speed. In order to improve the adaptive range of the flight speed of the propeller, the unmanned aerial vehicle pursuing the cruise efficiency generally adopts the design of a propeller pitch-variable scheme so as to give consideration to the high-low speed cruise performance.
With the continuous emergence of new structure aircrafts in recent years, a VTOL (VTOL) which has the functions of helicopter vertical take-off and landing and fixed wing high-performance cruise is subjected to more and more multiple views, which requires that a propeller has the characteristics of high thrust and low speed in the vertical take-off and landing stage and low thrust and high speed cruise in the level flight cruise stage, and the problems of low efficiency and huge energy consumption in the vertical take-off and landing stage generally exist at present.
Disclosure of Invention
The propeller push (pull) force required by the aircraft during low-speed flight is much larger than that of normal cruise flight, for example, the push (pull) force required during the vertical take-off and landing stage of the novel VTOL aircraft is several times larger than that required during the normal cruise stage.
According to the aerodynamics, the momentum theorem and the basic theory of the propeller, the diameter of the propeller is doubled under the condition of the same effective power, and the output thrust of the propeller is doubled, namely the power efficiency is doubled.
The invention provides a variable-configuration propeller structure and an aircraft, which flexibly change the configuration of a propeller through control of a control system, realize the optimal matching of the performance of a low-speed high-thrust working condition and a high-speed low-thrust working condition, use a large-diameter propeller disk propeller at a low speed, use a small-diameter propeller disk propeller at a high speed and give consideration to the flight performance of two typical working conditions.
In order to achieve the effect, the invention adopts the following technical scheme:
the variable-configuration propeller structure comprises a hub and blades distributed around the hub, wherein at least one blade is connected with the hub through a traction rope, and the diameter of the blade is adjusted through retraction and extension of the traction rope.
Further, the blades of adjustable diameter are evenly distributed around the hub.
Further, all the blades connected to the hub are distributed on the same horizontal plane. Alternatively, the fixed blade and the blade with the adjustable diameter are respectively positioned on different horizontal planes.
Further, this screw structure still includes rectification hood and connecting portion, the rectification hood with connecting portion all are connected with the propeller hub, the rectification hood is located the air incoming flow direction in propeller hub the place ahead, connecting portion are located the air outgoing flow direction behind the propeller hub.
Furthermore, a control actuator is arranged in the propeller hub and connected with the traction rope.
Furthermore, the control actuator is a servo motor or a steering engine.
Furthermore, the hauling cable is a steel wire rope.
The invention also provides an aircraft comprising the variable-configuration propeller structure in any one of the technical schemes.
The invention takes into account the propeller efficiency in the vertical take-off and landing stage and the cruise flight stage by changing the propeller configuration, namely, a large propeller disc configuration is adopted in the low-speed high-thrust stage, a small propeller disc configuration is adopted in the cruise low-thrust stage, and the propeller efficiency can be further improved by combining the use. The propeller configuration is dynamically controlled and adjusted by the control system in the flight process so as to match the thrust requirements of different flight modes and speeds, achieve the characteristics of high efficiency and high efficiency of the propeller system and reduce the flight power consumption.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a schematic structural view of a modified propeller according to an embodiment of the present invention;
FIG. 2 is a schematic view of a configuration of a propeller structure according to another embodiment of the present invention;
FIG. 3 is a schematic view of another configuration of a propeller structure according to yet another embodiment of the present invention;
FIG. 4 is a schematic view of the internal structure of an alternative propeller configuration;
description of reference numerals:
the wind power generator comprises 1-propeller hub, 2-propeller blade, 21-hauling rope, 3-rectifying hood, 4-connecting part and 5-control actuator.
Detailed Description
In order to make the technical solutions better understood by those skilled in the art, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are only partial embodiments of the present application, but not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
In the present application, the terms "upper", "lower", "left", "right", "front", "rear", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings. These terms are used primarily to better describe the present application and its embodiments, and are not used to limit the indicated devices, elements or components to a particular orientation or to be constructed and operated in a particular orientation. Moreover, some of the above terms may be used to indicate other meanings besides the orientation or positional relationship, for example, the term "on" may also be used to indicate some kind of attachment or connection relationship in some cases. The specific meaning of these terms in this application will be understood by those of ordinary skill in the art as appropriate.
As shown in fig. 1, the present embodiment provides a modified propeller structure, which includes a hub 1 and blades 2 distributed around the hub 1, wherein at least one blade 2 is connected to the hub 1 through a pulling rope 21, and the diameter of the blade 2 is adjusted by retracting the pulling rope 21.
It should be noted that, during the vertical lifting stage of the VTOL aircraft, the configuration of the propeller disk with a large diameter is adopted during the low-speed and high-thrust stage, and the configuration of the propeller disk with a small diameter is adopted during the cruising and low-thrust stage. That is, according to the embodiment of fig. 1, the length of the hauling cable 21 is increased in the low-speed or hovering working condition stage, so that the diameter of the blade 2 is increased, the area of the blade disc is enlarged, the force effect is improved, and the thrust is increased. The traction rope 21 is contracted under the working conditions of cruising and high-speed flight, so that the diameter of the paddle 2 is reduced, the area of a paddle disc is reduced, the force effect is reduced, and the thrust is reduced.
As can be seen in fig. 1, when there are more than two adjustable diameter blades 2, they are evenly distributed around the disc 1.
Generally, the present embodiment further includes a fairing cover 3 and a connecting portion 4, both the fairing cover 3 and the connecting portion 4 are connected to the hub 1, the fairing cover 3 is located in front of the hub 1, and the connecting portion 4 is located behind the disk 1. The fairing head housing 3 and attachment 4 are part of an aircraft and are typically connected to a propeller drive power system. The control actuator 5 is arranged in the hub 1, as shown in fig. 3, connected with the hauling cable 21 and used for controlling the hauling cable 21 to be retracted, and the rigid propeller blade 2 moves along the radial direction by means of the centrifugal force and the hauling force of the hauling cable 21, so that the rotating radius of the blade 2 and the area of a propeller disc are changed, and the force effect is changed. By controlling the change of the propeller system configuration and correspondingly adjusting the power output, the requirements of different speeds and push (pull) forces in flight are matched, the efficiency is improved, and the power consumption is reduced. In some embodiments, the common control actuator may be a servo motor or a steering engine.
Specifically, this embodiment describes two preferred embodiments. As shown in fig. 2, by controlling the connection arrangement of the hauling cable 21 and the hub 1, it is ensured that all the blades 2 connected to the hub 1 are distributed on the same horizontal plane, and the blades are divided into two groups, one group is fixed blades, the other group is blades with adjustable diameter, and the two groups of blades are staggered and uniformly distributed around the hub 1. Those skilled in the art will appreciate that the illustration in fig. 2 is merely one embodiment, by way of example. In practice, all the blades may be divided into a plurality of groups according to the number and the need, each group of blades being adjusted to a different diameter.
Another preferred embodiment is shown in fig. 3, where the fixed blade and the adjustable diameter blade are located in different horizontal planes. In fig. 3 it is shown that the fixed blades lie in one plane, and by controlling the arrangement of the attachment of the pulling rope 21 to the hub 1, it is ensured that the blades of adjustable diameter lie in another plane, so as to achieve a high efficiency of the proprotor aircraft. It will be appreciated by those skilled in the art that embodiments of the present invention are not so limited and that to address more complex flight requirements, the blades may be divided into groups, each group of blades being extendable to a different size, each distributed in a different horizontal plane.
The hauling cable in this embodiment is preferably a relatively thin steel cable.
The present application also includes an aircraft including any of the modified propeller configurations described in the embodiments above. Common aircraft include helicopters or VTOL aircraft.
The above description is only a preferred embodiment of the present application and is not intended to limit the present application, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, improvement and the like made within the spirit and principle of the present application shall be included in the protection scope of the present application.
Claims (9)
1. The variable-configuration propeller structure is characterized by comprising a hub and blades distributed around the hub, wherein at least one blade is connected with the hub through a traction rope, and the diameter of the blade is adjusted through retraction and extension of the traction rope.
2. A modified propeller structure as in claim 1 wherein the blades of adjustable diameter are evenly distributed around the hub.
3. A modified propeller structure as claimed in claim 2 wherein all the blades connected to the hub are distributed in the same horizontal plane.
4. A reconfigured propeller structure as claimed in claim 2 in which the fixed blades and the adjustable diameter blades are located at different levels.
5. The variable configuration propeller structure of claim 1 further comprising a fairing cap and a connecting portion, both of which are connected to the hub, the fairing cap being located in an air inflow direction forward of the hub and the connecting portion being located in an air outflow direction aft of the hub.
6. The reconfigurable propeller structure of claim 1, wherein a control actuator is disposed within the hub and coupled to the tow line.
7. A variable configuration propeller structure as claimed in claim 6, wherein the control actuator is a servo motor or a steering engine.
8. A reconfigured propeller structure as claimed in claim 1 in which said tow line is a wire rope.
9. An aircraft comprising a modified propeller structure as claimed in any one of claims 1 to 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110843267.7A CN113548174A (en) | 2021-07-26 | 2021-07-26 | Variable-configuration propeller structure and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110843267.7A CN113548174A (en) | 2021-07-26 | 2021-07-26 | Variable-configuration propeller structure and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113548174A true CN113548174A (en) | 2021-10-26 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110843267.7A Pending CN113548174A (en) | 2021-07-26 | 2021-07-26 | Variable-configuration propeller structure and aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113548174A (en) |
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2021
- 2021-07-26 CN CN202110843267.7A patent/CN113548174A/en active Pending
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Application publication date: 20211026 |
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| RJ01 | Rejection of invention patent application after publication |